HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il) Reynolds number: 500,000 Max Cl/Cd: 75.56 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1012-il-500000.txt Download as CSV file: xf-hq1012-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8407 0.08454 0.08171 -0.0297 1.0000 0.0102
-14.500 -0.8657 0.07486 0.07183 -0.0363 1.0000 0.0101
-14.250 -0.8851 0.06721 0.06400 -0.0415 1.0000 0.0100
-14.000 -0.9092 0.05968 0.05630 -0.0463 1.0000 0.0102
-13.750 -0.9238 0.05425 0.05070 -0.0495 1.0000 0.0102
-13.500 -0.9358 0.04960 0.04586 -0.0517 1.0000 0.0101
-13.250 -0.9516 0.04490 0.04099 -0.0534 1.0000 0.0102
-13.000 -0.9569 0.04176 0.03768 -0.0540 1.0000 0.0101
-12.750 -0.9664 0.03839 0.03417 -0.0542 1.0000 0.0104
-12.500 -0.9682 0.03605 0.03172 -0.0538 1.0000 0.0105
-12.250 -0.9696 0.03391 0.02946 -0.0529 1.0000 0.0107
-12.000 -0.9674 0.03232 0.02778 -0.0518 1.0000 0.0109
-11.750 -0.9658 0.03079 0.02614 -0.0501 1.0000 0.0112
-11.500 -0.9629 0.02955 0.02478 -0.0478 1.0000 0.0115
-11.250 -0.9591 0.02827 0.02338 -0.0453 1.0000 0.0118
-11.000 -0.9508 0.02685 0.02180 -0.0433 1.0000 0.0121
-10.750 -0.9402 0.02549 0.02028 -0.0415 1.0000 0.0125
-10.500 -0.9276 0.02423 0.01886 -0.0398 1.0000 0.0128
-10.250 -0.9130 0.02316 0.01765 -0.0383 1.0000 0.0131
-10.000 -0.9036 0.02137 0.01571 -0.0361 1.0000 0.0136
-9.750 -0.8905 0.02018 0.01445 -0.0343 1.0000 0.0142
-9.500 -0.8741 0.01942 0.01365 -0.0328 1.0000 0.0149
-9.250 -0.8574 0.01870 0.01288 -0.0312 1.0000 0.0157
-9.000 -0.8412 0.01799 0.01209 -0.0294 1.0000 0.0165
-8.750 -0.8244 0.01745 0.01147 -0.0276 1.0000 0.0173
-8.500 -0.8160 0.01643 0.01042 -0.0247 1.0000 0.0188
-8.250 -0.7906 0.01600 0.00999 -0.0248 0.9981 0.0209
-8.000 -0.7549 0.01522 0.00913 -0.0270 0.9936 0.0236
-7.750 -0.7207 0.01456 0.00848 -0.0288 0.9881 0.0278
-7.500 -0.6850 0.01383 0.00773 -0.0310 0.9838 0.0333
-7.250 -0.6485 0.01360 0.00746 -0.0330 0.9788 0.0381
-7.000 -0.6144 0.01293 0.00681 -0.0348 0.9723 0.0447
-6.750 -0.5793 0.01263 0.00645 -0.0365 0.9653 0.0490
-6.500 -0.5470 0.01206 0.00589 -0.0378 0.9565 0.0559
-6.250 -0.5167 0.01180 0.00556 -0.0384 0.9452 0.0605
-6.000 -0.4901 0.01131 0.00509 -0.0383 0.9329 0.0690
-5.750 -0.4643 0.01096 0.00472 -0.0380 0.9211 0.0780
-5.500 -0.4393 0.01064 0.00437 -0.0374 0.9102 0.0893
-5.250 -0.4153 0.01026 0.00404 -0.0367 0.8989 0.1074
-5.000 -0.3914 0.00985 0.00372 -0.0361 0.8886 0.1373
-4.750 -0.3674 0.00943 0.00346 -0.0355 0.8793 0.1826
-4.500 -0.3429 0.00907 0.00322 -0.0350 0.8699 0.2268
-4.250 -0.3182 0.00871 0.00299 -0.0346 0.8614 0.2711
-4.000 -0.2943 0.00826 0.00275 -0.0340 0.8532 0.3321
-3.750 -0.2703 0.00781 0.00257 -0.0335 0.8449 0.4084
-3.500 -0.2455 0.00751 0.00243 -0.0329 0.8375 0.4718
-3.250 -0.2198 0.00730 0.00237 -0.0325 0.8295 0.5222
-3.000 -0.1934 0.00720 0.00232 -0.0321 0.8226 0.5589
-2.750 -0.1662 0.00714 0.00228 -0.0319 0.8147 0.5842
-2.500 -0.1391 0.00712 0.00224 -0.0316 0.8078 0.6040
-2.250 -0.1117 0.00709 0.00222 -0.0314 0.8002 0.6231
-2.000 -0.0842 0.00710 0.00219 -0.0311 0.7935 0.6406
-1.750 -0.0566 0.00710 0.00219 -0.0309 0.7865 0.6555
-1.500 -0.0291 0.00710 0.00218 -0.0307 0.7793 0.6700
-1.250 -0.0016 0.00709 0.00217 -0.0304 0.7710 0.6808
-1.000 0.0261 0.00710 0.00212 -0.0303 0.7627 0.6899
-0.750 0.0538 0.00709 0.00211 -0.0301 0.7540 0.6986
-0.500 0.0815 0.00710 0.00209 -0.0299 0.7468 0.7076
-0.250 0.1094 0.00711 0.00209 -0.0298 0.7383 0.7176
0.000 0.1369 0.00711 0.00209 -0.0296 0.7304 0.7261
0.250 0.1647 0.00711 0.00210 -0.0294 0.7218 0.7349
0.500 0.1923 0.00712 0.00211 -0.0292 0.7131 0.7439
0.750 0.2198 0.00713 0.00211 -0.0290 0.7042 0.7526
1.000 0.2477 0.00714 0.00213 -0.0289 0.6957 0.7612
1.250 0.2752 0.00715 0.00214 -0.0287 0.6878 0.7678
1.500 0.3031 0.00716 0.00217 -0.0286 0.6778 0.7754
1.750 0.3306 0.00716 0.00219 -0.0285 0.6685 0.7822
2.000 0.3581 0.00720 0.00222 -0.0283 0.6585 0.7901
2.250 0.3854 0.00720 0.00225 -0.0281 0.6467 0.7974
2.500 0.4128 0.00723 0.00229 -0.0279 0.6339 0.8060
2.750 0.4395 0.00724 0.00233 -0.0275 0.6189 0.8138
3.000 0.4663 0.00729 0.00237 -0.0272 0.6017 0.8228
3.250 0.4925 0.00734 0.00242 -0.0268 0.5824 0.8315
3.500 0.5184 0.00741 0.00248 -0.0263 0.5580 0.8409
3.750 0.5434 0.00756 0.00255 -0.0257 0.5243 0.8516
4.000 0.5673 0.00774 0.00266 -0.0249 0.4852 0.8625
4.250 0.5906 0.00799 0.00280 -0.0240 0.4438 0.8749
4.500 0.6128 0.00831 0.00299 -0.0229 0.3961 0.8902
4.750 0.6348 0.00865 0.00321 -0.0218 0.3497 0.9093
5.000 0.6598 0.00900 0.00346 -0.0214 0.3095 0.9349
5.250 0.6944 0.00943 0.00377 -0.0232 0.2772 0.9629
5.500 0.7342 0.00980 0.00407 -0.0261 0.2530 0.9872
5.750 0.7653 0.01015 0.00434 -0.0272 0.2341 1.0000
6.000 0.7885 0.01045 0.00458 -0.0265 0.2181 1.0000
6.250 0.8123 0.01075 0.00484 -0.0259 0.2002 1.0000
6.500 0.8357 0.01110 0.00511 -0.0253 0.1779 1.0000
6.750 0.8583 0.01152 0.00542 -0.0246 0.1531 1.0000
7.000 0.8800 0.01203 0.00579 -0.0238 0.1277 1.0000
7.250 0.9014 0.01257 0.00622 -0.0229 0.1077 1.0000
7.500 0.9230 0.01309 0.00667 -0.0220 0.0932 1.0000
7.750 0.9450 0.01357 0.00712 -0.0212 0.0823 1.0000
8.000 0.9670 0.01403 0.00758 -0.0204 0.0736 1.0000
8.250 0.9879 0.01458 0.00809 -0.0195 0.0654 1.0000
8.500 1.0096 0.01504 0.00855 -0.0186 0.0581 1.0000
8.750 1.0309 0.01552 0.00905 -0.0178 0.0521 1.0000
9.000 1.0513 0.01606 0.00957 -0.0168 0.0464 1.0000
9.250 1.0721 0.01654 0.01008 -0.0158 0.0413 1.0000
9.500 1.0912 0.01714 0.01066 -0.0147 0.0363 1.0000
9.750 1.1106 0.01769 0.01125 -0.0136 0.0320 1.0000
10.000 1.1267 0.01845 0.01200 -0.0121 0.0274 1.0000
10.250 1.1446 0.01903 0.01264 -0.0107 0.0240 1.0000
10.500 1.1551 0.02000 0.01360 -0.0084 0.0203 1.0000
10.750 1.1686 0.02065 0.01433 -0.0064 0.0182 1.0000
11.000 1.1764 0.02165 0.01534 -0.0038 0.0161 1.0000
11.250 1.1828 0.02276 0.01655 -0.0011 0.0146 1.0000
11.500 1.1929 0.02369 0.01755 0.0008 0.0135 1.0000
11.750 1.2004 0.02483 0.01874 0.0028 0.0123 1.0000
12.000 1.1997 0.02658 0.02058 0.0053 0.0117 1.0000
12.250 1.2061 0.02794 0.02205 0.0069 0.0111 1.0000
12.500 1.2116 0.02944 0.02367 0.0084 0.0107 1.0000
12.750 1.2154 0.03115 0.02548 0.0097 0.0106 1.0000
13.000 1.2199 0.03288 0.02731 0.0108 0.0099 1.0000
13.250 1.2218 0.03492 0.02945 0.0118 0.0096 1.0000
13.500 1.2248 0.03694 0.03154 0.0124 0.0093 1.0000
13.750 1.2237 0.03946 0.03417 0.0130 0.0092 1.0000
14.000 1.2212 0.04224 0.03706 0.0133 0.0090 1.0000
14.250 1.2173 0.04532 0.04025 0.0132 0.0089 1.0000
14.500 1.2086 0.04908 0.04413 0.0130 0.0087 1.0000
14.750 1.1934 0.05386 0.04907 0.0122 0.0084 1.0000
15.000 1.1878 0.05767 0.05302 0.0112 0.0084 1.0000
15.250 1.1827 0.06169 0.05719 0.0098 0.0083 1.0000
15.500 1.1759 0.06613 0.06178 0.0081 0.0083 1.0000
15.750 1.1668 0.07114 0.06694 0.0060 0.0083 1.0000
16.000 1.1581 0.07641 0.07236 0.0034 0.0082 1.0000
16.250 1.1472 0.08214 0.07824 0.0006 0.0082 1.0000
16.500 1.1347 0.08851 0.08476 -0.0028 0.0082 1.0000
16.750 1.1220 0.09507 0.09147 -0.0064 0.0082 1.0000
17.000 1.1078 0.10222 0.09877 -0.0104 0.0081 1.0000
17.250 1.0939 0.10954 0.10623 -0.0146 0.0081 1.0000
17.500 1.0779 0.11734 0.11417 -0.0190 0.0082 1.0000
17.750 1.0628 0.12530 0.12226 -0.0237 0.0082 1.0000
18.000 1.0446 0.13422 0.13133 -0.0291 0.0082 1.0000
18.250 1.0285 0.14289 0.14012 -0.0343 0.0082 1.0000
18.500 1.0090 0.15264 0.14999 -0.0401 0.0083 1.0000
18.750 0.9834 0.16449 0.16199 -0.0472 0.0084 1.0000
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