HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.63 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1012-il-1000000-n5.txt Download as CSV file: xf-hq1012-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9227 0.11773 0.11541 -0.0097 1.0000 0.0038
-17.250 -0.9919 0.09980 0.09727 -0.0194 1.0000 0.0037
-17.000 -1.0477 0.08502 0.08228 -0.0275 1.0000 0.0035
-16.750 -1.0838 0.07397 0.07104 -0.0339 1.0000 0.0034
-16.500 -1.1105 0.06516 0.06206 -0.0393 1.0000 0.0034
-16.250 -1.1380 0.05690 0.05362 -0.0445 1.0000 0.0035
-16.000 -1.1525 0.05130 0.04788 -0.0476 1.0000 0.0034
-15.750 -1.1682 0.04601 0.04244 -0.0503 1.0000 0.0034
-15.500 -1.1726 0.04251 0.03883 -0.0518 1.0000 0.0034
-15.250 -1.1845 0.03840 0.03457 -0.0531 1.0000 0.0035
-15.000 -1.1878 0.03551 0.03156 -0.0536 1.0000 0.0035
-14.750 -1.1895 0.03296 0.02890 -0.0537 1.0000 0.0035
-14.500 -1.1898 0.03073 0.02656 -0.0534 1.0000 0.0036
-14.250 -1.1854 0.02905 0.02480 -0.0528 1.0000 0.0038
-14.000 -1.1806 0.02753 0.02320 -0.0519 1.0000 0.0038
-13.750 -1.1759 0.02612 0.02171 -0.0507 1.0000 0.0039
-13.500 -1.1723 0.02479 0.02027 -0.0490 1.0000 0.0040
-13.250 -1.1650 0.02385 0.01926 -0.0471 1.0000 0.0040
-13.000 -1.1588 0.02295 0.01827 -0.0446 1.0000 0.0041
-12.750 -1.1491 0.02219 0.01744 -0.0424 1.0000 0.0043
-12.500 -1.1358 0.02139 0.01656 -0.0409 1.0000 0.0044
-12.250 -1.1208 0.02063 0.01574 -0.0394 1.0000 0.0045
-12.000 -1.1049 0.01990 0.01493 -0.0381 1.0000 0.0046
-11.750 -1.0876 0.01923 0.01419 -0.0369 1.0000 0.0048
-11.500 -1.0694 0.01861 0.01351 -0.0357 1.0000 0.0049
-11.250 -1.0503 0.01806 0.01289 -0.0347 1.0000 0.0050
-11.000 -1.0326 0.01735 0.01212 -0.0334 1.0000 0.0053
-10.750 -1.0143 0.01669 0.01139 -0.0321 1.0000 0.0056
-10.500 -0.9951 0.01613 0.01080 -0.0310 1.0000 0.0059
-10.250 -0.9706 0.01558 0.01021 -0.0308 0.9964 0.0062
-10.000 -0.9398 0.01505 0.00963 -0.0320 0.9874 0.0066
-9.750 -0.9069 0.01453 0.00906 -0.0336 0.9783 0.0070
-9.500 -0.8729 0.01405 0.00852 -0.0354 0.9676 0.0074
-9.250 -0.8415 0.01346 0.00787 -0.0366 0.9514 0.0081
-8.750 -0.7901 0.01271 0.00695 -0.0363 0.9069 0.0095
-8.500 -0.7663 0.01241 0.00656 -0.0356 0.8913 0.0102
-8.250 -0.7425 0.01208 0.00616 -0.0350 0.8776 0.0115
-8.000 -0.7184 0.01176 0.00579 -0.0344 0.8656 0.0132
-7.500 -0.6689 0.01116 0.00511 -0.0335 0.8453 0.0188
-7.250 -0.6438 0.01087 0.00482 -0.0332 0.8366 0.0228
-7.000 -0.6179 0.01066 0.00456 -0.0329 0.8280 0.0251
-6.750 -0.5920 0.01041 0.00429 -0.0326 0.8200 0.0285
-6.500 -0.5660 0.01019 0.00404 -0.0323 0.8119 0.0319
-6.250 -0.5394 0.01000 0.00382 -0.0322 0.8043 0.0341
-6.000 -0.5132 0.00979 0.00358 -0.0319 0.7968 0.0382
-5.750 -0.4864 0.00959 0.00338 -0.0318 0.7895 0.0417
-5.500 -0.4598 0.00941 0.00316 -0.0316 0.7824 0.0468
-5.250 -0.4330 0.00920 0.00297 -0.0314 0.7758 0.0541
-5.000 -0.4063 0.00901 0.00278 -0.0313 0.7687 0.0620
-4.750 -0.3792 0.00883 0.00260 -0.0312 0.7623 0.0696
-4.500 -0.3522 0.00865 0.00243 -0.0311 0.7555 0.0794
-4.250 -0.3252 0.00847 0.00226 -0.0309 0.7493 0.0914
-4.000 -0.2981 0.00828 0.00211 -0.0309 0.7425 0.1060
-3.750 -0.2712 0.00809 0.00196 -0.0307 0.7360 0.1246
-3.500 -0.2442 0.00787 0.00181 -0.0307 0.7287 0.1497
-3.250 -0.2174 0.00767 0.00168 -0.0305 0.7214 0.1773
-3.000 -0.1901 0.00748 0.00156 -0.0305 0.7140 0.2031
-2.750 -0.1632 0.00728 0.00144 -0.0304 0.7074 0.2371
-2.500 -0.1361 0.00705 0.00133 -0.0303 0.7012 0.2716
-2.250 -0.1096 0.00680 0.00121 -0.0302 0.6931 0.3174
-2.000 -0.0832 0.00651 0.00110 -0.0300 0.6831 0.3805
-1.750 -0.0563 0.00632 0.00102 -0.0299 0.6729 0.4248
-1.500 -0.0298 0.00610 0.00096 -0.0298 0.6641 0.4795
-1.250 -0.0023 0.00597 0.00092 -0.0297 0.6557 0.5180
-1.000 0.0251 0.00587 0.00091 -0.0296 0.6477 0.5523
-0.750 0.0532 0.00583 0.00090 -0.0296 0.6389 0.5723
-0.500 0.0813 0.00583 0.00089 -0.0296 0.6288 0.5839
-0.250 0.1093 0.00584 0.00088 -0.0296 0.6186 0.5959
0.000 0.1375 0.00585 0.00089 -0.0296 0.6072 0.6082
0.250 0.1655 0.00587 0.00090 -0.0296 0.5933 0.6198
0.500 0.1935 0.00590 0.00091 -0.0296 0.5801 0.6304
0.750 0.2215 0.00593 0.00094 -0.0296 0.5681 0.6399
1.000 0.2494 0.00599 0.00097 -0.0295 0.5527 0.6493
1.250 0.2769 0.00606 0.00101 -0.0295 0.5341 0.6582
1.500 0.3045 0.00615 0.00105 -0.0294 0.5148 0.6672
1.750 0.3317 0.00628 0.00111 -0.0293 0.4897 0.6756
2.000 0.3585 0.00644 0.00119 -0.0291 0.4599 0.6816
2.250 0.3849 0.00667 0.00129 -0.0289 0.4216 0.6879
2.500 0.4111 0.00691 0.00140 -0.0286 0.3850 0.6938
2.750 0.4371 0.00716 0.00153 -0.0284 0.3453 0.7004
3.000 0.4624 0.00751 0.00169 -0.0280 0.2983 0.7071
3.250 0.4879 0.00780 0.00186 -0.0277 0.2628 0.7142
3.500 0.5147 0.00798 0.00199 -0.0275 0.2460 0.7215
3.750 0.5417 0.00811 0.00212 -0.0274 0.2355 0.7284
4.000 0.5687 0.00825 0.00225 -0.0273 0.2249 0.7357
4.250 0.5956 0.00839 0.00238 -0.0271 0.2140 0.7424
4.500 0.6221 0.00858 0.00253 -0.0270 0.1987 0.7500
4.750 0.6482 0.00877 0.00270 -0.0267 0.1824 0.7571
5.000 0.6744 0.00897 0.00286 -0.0265 0.1671 0.7649
5.250 0.7002 0.00919 0.00306 -0.0262 0.1512 0.7725
5.500 0.7254 0.00947 0.00328 -0.0258 0.1312 0.7810
5.750 0.7501 0.00976 0.00352 -0.0253 0.1140 0.7896
6.000 0.7752 0.01002 0.00376 -0.0250 0.1013 0.7986
6.250 0.7999 0.01030 0.00401 -0.0245 0.0881 0.8086
6.500 0.8242 0.01059 0.00429 -0.0240 0.0759 0.8190
6.750 0.8487 0.01085 0.00456 -0.0234 0.0665 0.8304
7.000 0.8725 0.01114 0.00484 -0.0228 0.0571 0.8434
7.250 0.8959 0.01142 0.00514 -0.0221 0.0497 0.8587
7.500 0.9195 0.01160 0.00541 -0.0214 0.0460 0.8797
7.750 0.9408 0.01184 0.00574 -0.0202 0.0390 0.9190
8.000 0.9821 0.01218 0.00613 -0.0235 0.0340 1.0000
8.250 1.0053 0.01255 0.00648 -0.0228 0.0293 1.0000
8.500 1.0286 0.01290 0.00682 -0.0222 0.0258 1.0000
8.750 1.0511 0.01330 0.00722 -0.0215 0.0219 1.0000
9.000 1.0735 0.01371 0.00762 -0.0207 0.0184 1.0000
9.250 1.0953 0.01415 0.00804 -0.0199 0.0156 1.0000
9.500 1.1164 0.01463 0.00851 -0.0190 0.0129 1.0000
9.750 1.1376 0.01508 0.00898 -0.0181 0.0107 1.0000
10.000 1.1576 0.01560 0.00950 -0.0171 0.0086 1.0000
10.250 1.1772 0.01612 0.01005 -0.0160 0.0068 1.0000
10.500 1.1963 0.01666 0.01061 -0.0148 0.0057 1.0000
10.750 1.2148 0.01720 0.01118 -0.0136 0.0051 1.0000
11.000 1.2317 0.01781 0.01181 -0.0121 0.0044 1.0000
11.250 1.2476 0.01837 0.01242 -0.0105 0.0041 1.0000
11.500 1.2610 0.01895 0.01306 -0.0084 0.0039 1.0000
11.750 1.2740 0.01954 0.01370 -0.0063 0.0038 1.0000
12.000 1.2856 0.02023 0.01445 -0.0042 0.0035 1.0000
12.250 1.2975 0.02093 0.01522 -0.0023 0.0034 1.0000
12.500 1.3076 0.02178 0.01613 -0.0003 0.0033 1.0000
12.750 1.3176 0.02267 0.01709 0.0016 0.0032 1.0000
13.000 1.3267 0.02367 0.01816 0.0033 0.0031 1.0000
13.250 1.3347 0.02479 0.01934 0.0050 0.0030 1.0000
13.500 1.3419 0.02602 0.02066 0.0066 0.0029 1.0000
13.750 1.3478 0.02740 0.02213 0.0081 0.0028 1.0000
14.000 1.3497 0.02919 0.02402 0.0096 0.0027 1.0000
14.250 1.3567 0.03062 0.02553 0.0106 0.0026 1.0000
14.500 1.3606 0.03239 0.02739 0.0115 0.0026 1.0000
14.750 1.3649 0.03420 0.02929 0.0123 0.0026 1.0000
15.000 1.3657 0.03641 0.03162 0.0129 0.0026 1.0000
15.250 1.3678 0.03860 0.03391 0.0133 0.0025 1.0000
15.500 1.3689 0.04099 0.03639 0.0134 0.0025 1.0000
15.750 1.3672 0.04379 0.03929 0.0134 0.0024 1.0000
16.000 1.3638 0.04691 0.04252 0.0130 0.0025 1.0000
16.250 1.3572 0.05057 0.04631 0.0123 0.0024 1.0000
16.500 1.3498 0.05458 0.05044 0.0111 0.0024 1.0000
16.750 1.3430 0.05875 0.05472 0.0097 0.0024 1.0000
17.000 1.3316 0.06385 0.05995 0.0076 0.0023 1.0000
17.250 1.3191 0.06941 0.06564 0.0050 0.0024 1.0000
17.500 1.3024 0.07597 0.07235 0.0017 0.0023 1.0000
17.750 1.2859 0.08282 0.07933 -0.0019 0.0024 1.0000
18.000 1.2577 0.09214 0.08883 -0.0069 0.0023 1.0000
18.250 1.2308 0.10160 0.09846 -0.0122 0.0023 1.0000
18.500 1.1997 0.11209 0.10910 -0.0180 0.0024 1.0000
18.750 1.1708 0.12239 0.11954 -0.0238 0.0024 1.0000
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