HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.93 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1010-il-1000000.txt Download as CSV file: xf-hq1010-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/10 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7790 0.05063 0.04875 -0.0427 1.0000 0.0056
-11.000 -0.8045 0.04440 0.04233 -0.0466 1.0000 0.0056
-10.750 -0.8697 0.03641 0.03388 -0.0447 1.0000 0.0053
-10.500 -0.8926 0.03143 0.02847 -0.0416 1.0000 0.0052
-10.250 -0.8965 0.02775 0.02441 -0.0392 1.0000 0.0051
-10.000 -0.8901 0.02508 0.02144 -0.0374 1.0000 0.0051
-9.750 -0.8782 0.02308 0.01920 -0.0359 1.0000 0.0052
-9.500 -0.8633 0.02144 0.01736 -0.0345 1.0000 0.0053
-9.250 -0.8464 0.02008 0.01583 -0.0333 1.0000 0.0054
-9.000 -0.8280 0.01900 0.01462 -0.0321 1.0000 0.0057
-8.750 -0.8098 0.01786 0.01334 -0.0308 1.0000 0.0059
-8.500 -0.7905 0.01697 0.01232 -0.0296 1.0000 0.0062
-8.250 -0.7709 0.01616 0.01140 -0.0283 1.0000 0.0065
-8.000 -0.7516 0.01542 0.01057 -0.0269 1.0000 0.0067
-7.750 -0.7317 0.01496 0.01005 -0.0256 1.0000 0.0069
-7.500 -0.7025 0.01369 0.00863 -0.0265 0.9975 0.0072
-7.250 -0.6705 0.01240 0.00718 -0.0280 0.9935 0.0078
-7.000 -0.6384 0.01172 0.00644 -0.0292 0.9888 0.0084
-6.750 -0.6042 0.01119 0.00585 -0.0309 0.9849 0.0092
-6.500 -0.5700 0.01079 0.00542 -0.0324 0.9800 0.0102
-6.250 -0.5377 0.01011 0.00465 -0.0336 0.9723 0.0121
-6.000 -0.5059 0.00969 0.00421 -0.0346 0.9628 0.0144
-5.750 -0.4766 0.00925 0.00375 -0.0350 0.9502 0.0194
-5.500 -0.4498 0.00893 0.00343 -0.0348 0.9352 0.0281
-5.250 -0.4235 0.00874 0.00319 -0.0344 0.9207 0.0342
-5.000 -0.3976 0.00854 0.00298 -0.0340 0.9077 0.0413
-4.750 -0.3716 0.00836 0.00276 -0.0336 0.8960 0.0483
-4.500 -0.3451 0.00821 0.00257 -0.0333 0.8852 0.0548
-4.250 -0.3188 0.00799 0.00236 -0.0331 0.8750 0.0676
-4.000 -0.2927 0.00771 0.00215 -0.0328 0.8656 0.0917
-3.500 -0.2411 0.00701 0.00176 -0.0323 0.8473 0.1908
-3.250 -0.2149 0.00671 0.00160 -0.0320 0.8388 0.2396
-3.000 -0.1889 0.00639 0.00144 -0.0318 0.8297 0.2960
-2.750 -0.1637 0.00589 0.00127 -0.0316 0.8209 0.3998
-2.500 -0.1377 0.00559 0.00117 -0.0313 0.8129 0.4716
-2.250 -0.1107 0.00540 0.00110 -0.0312 0.8045 0.5201
-2.000 -0.0835 0.00529 0.00105 -0.0310 0.7957 0.5559
-1.500 -0.0288 0.00514 0.00098 -0.0306 0.7750 0.6164
-1.250 -0.0011 0.00510 0.00095 -0.0305 0.7655 0.6350
-1.000 0.0264 0.00509 0.00094 -0.0304 0.7559 0.6566
-0.750 0.0542 0.00506 0.00093 -0.0303 0.7460 0.6739
-0.500 0.0821 0.00506 0.00092 -0.0302 0.7359 0.6868
-0.250 0.1099 0.00507 0.00091 -0.0301 0.7251 0.6976
0.250 0.1657 0.00507 0.00092 -0.0300 0.7048 0.7196
0.500 0.1937 0.00509 0.00093 -0.0299 0.6948 0.7304
0.750 0.2215 0.00512 0.00095 -0.0298 0.6846 0.7411
1.000 0.2491 0.00513 0.00097 -0.0297 0.6731 0.7521
1.250 0.2769 0.00515 0.00101 -0.0296 0.6610 0.7629
1.500 0.3046 0.00520 0.00103 -0.0295 0.6467 0.7725
1.750 0.3319 0.00525 0.00107 -0.0294 0.6297 0.7813
2.000 0.3594 0.00530 0.00110 -0.0292 0.6104 0.7901
2.250 0.3866 0.00539 0.00116 -0.0291 0.5886 0.7998
2.500 0.4133 0.00549 0.00122 -0.0288 0.5605 0.8095
2.750 0.4393 0.00568 0.00129 -0.0284 0.5186 0.8197
3.000 0.4650 0.00590 0.00139 -0.0281 0.4742 0.8308
3.250 0.4906 0.00613 0.00152 -0.0277 0.4315 0.8429
3.500 0.5154 0.00643 0.00167 -0.0271 0.3782 0.8565
3.750 0.5391 0.00680 0.00186 -0.0265 0.3175 0.8725
4.000 0.5630 0.00707 0.00204 -0.0257 0.2775 0.8940
4.500 0.6228 0.00740 0.00240 -0.0267 0.2318 0.9704
4.750 0.6625 0.00771 0.00260 -0.0296 0.2007 1.0000
5.000 0.6872 0.00803 0.00279 -0.0292 0.1715 1.0000
5.250 0.7115 0.00842 0.00304 -0.0287 0.1397 1.0000
5.500 0.7358 0.00882 0.00330 -0.0282 0.1122 1.0000
5.750 0.7601 0.00923 0.00359 -0.0277 0.0876 1.0000
6.000 0.7847 0.00960 0.00388 -0.0273 0.0692 1.0000
6.250 0.8095 0.00996 0.00417 -0.0269 0.0561 1.0000
6.500 0.8344 0.01030 0.00449 -0.0265 0.0462 1.0000
6.750 0.8590 0.01068 0.00482 -0.0260 0.0366 1.0000
7.000 0.8833 0.01109 0.00518 -0.0255 0.0276 1.0000
7.250 0.9079 0.01146 0.00553 -0.0251 0.0221 1.0000
7.500 0.9318 0.01192 0.00595 -0.0246 0.0160 1.0000
7.750 0.9550 0.01245 0.00648 -0.0239 0.0110 1.0000
8.000 0.9775 0.01309 0.00716 -0.0231 0.0082 1.0000
8.250 1.0010 0.01357 0.00769 -0.0225 0.0073 1.0000
8.500 1.0238 0.01412 0.00828 -0.0218 0.0065 1.0000
8.750 1.0432 0.01509 0.00935 -0.0205 0.0057 1.0000
9.000 1.0646 0.01577 0.01011 -0.0196 0.0055 1.0000
9.250 1.0859 0.01641 0.01083 -0.0188 0.0053 1.0000
9.500 1.1064 0.01713 0.01163 -0.0178 0.0050 1.0000
9.750 1.1259 0.01791 0.01251 -0.0167 0.0047 1.0000
10.000 1.1442 0.01880 0.01349 -0.0154 0.0045 1.0000
10.250 1.1616 0.01971 0.01449 -0.0141 0.0043 1.0000
10.500 1.1771 0.02075 0.01564 -0.0125 0.0042 1.0000
10.750 1.1910 0.02187 0.01688 -0.0108 0.0041 1.0000
11.000 1.2030 0.02307 0.01820 -0.0089 0.0041 1.0000
11.250 1.2112 0.02445 0.01971 -0.0065 0.0039 1.0000
11.500 1.2165 0.02563 0.02100 -0.0036 0.0039 1.0000
11.750 1.2176 0.02708 0.02258 -0.0005 0.0038 1.0000
12.000 1.2149 0.02897 0.02462 0.0026 0.0037 1.0000
12.250 1.2088 0.03125 0.02707 0.0053 0.0036 1.0000
12.500 1.2025 0.03375 0.02977 0.0074 0.0036 1.0000
12.750 1.2001 0.03606 0.03222 0.0088 0.0037 1.0000
13.000 1.1832 0.04007 0.03645 0.0099 0.0036 1.0000
13.250 1.1748 0.04346 0.04001 0.0101 0.0036 1.0000
13.500 1.1618 0.04772 0.04445 0.0095 0.0036 1.0000
13.750 1.1504 0.05215 0.04904 0.0082 0.0036 1.0000
14.000 1.1386 0.05706 0.05409 0.0062 0.0036 1.0000
14.250 1.1259 0.06257 0.05975 0.0034 0.0036 1.0000
14.500 1.1178 0.06779 0.06509 0.0004 0.0036 1.0000
14.750 1.0996 0.07532 0.07278 -0.0042 0.0036 1.0000
15.000 1.0816 0.08348 0.08108 -0.0093 0.0036 1.0000
15.250 1.0708 0.09061 0.08832 -0.0137 0.0036 1.0000
15.500 1.0531 0.09948 0.09731 -0.0191 0.0037 1.0000
15.750 1.0366 0.10826 0.10620 -0.0243 0.0037 1.0000
16.000 1.0184 0.11758 0.11561 -0.0297 0.0037 1.0000
16.250 0.9930 0.12928 0.12744 -0.0362 0.0039 1.0000
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