HQ 1.0/8 AIRFOIL (hq108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/8 AIRFOIL (hq108-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.19 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq108-il-1000000-n5.txt Download as CSV file: xf-hq108-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/8 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6066 0.08497 0.08343 -0.0103 1.0000 0.0015
-9.500 -0.6209 0.07737 0.07587 -0.0150 1.0000 0.0015
-9.250 -0.6368 0.06941 0.06794 -0.0213 1.0000 0.0015
-8.750 -0.7702 0.02736 0.02455 -0.0342 1.0000 0.0015
-8.500 -0.7603 0.02323 0.01994 -0.0330 1.0000 0.0015
-8.250 -0.7415 0.02141 0.01788 -0.0323 1.0000 0.0016
-8.000 -0.7219 0.01980 0.01603 -0.0315 1.0000 0.0017
-7.750 -0.6999 0.01889 0.01498 -0.0308 1.0000 0.0017
-7.500 -0.6854 0.01575 0.01135 -0.0292 1.0000 0.0019
-7.250 -0.6640 0.01475 0.01022 -0.0283 1.0000 0.0021
-7.000 -0.6352 0.01394 0.00928 -0.0289 0.9967 0.0022
-6.750 -0.6047 0.01327 0.00852 -0.0299 0.9919 0.0024
-6.500 -0.5736 0.01247 0.00760 -0.0309 0.9866 0.0025
-6.250 -0.5427 0.01178 0.00679 -0.0318 0.9804 0.0027
-6.000 -0.5109 0.01111 0.00601 -0.0329 0.9734 0.0030
-5.750 -0.4801 0.01071 0.00555 -0.0338 0.9638 0.0034
-5.500 -0.4502 0.01030 0.00508 -0.0343 0.9517 0.0037
-5.250 -0.4225 0.00986 0.00454 -0.0343 0.9363 0.0039
-5.000 -0.3972 0.00920 0.00370 -0.0338 0.9198 0.0046
-4.500 -0.3453 0.00859 0.00291 -0.0330 0.8927 0.0066
-4.250 -0.3188 0.00838 0.00260 -0.0327 0.8808 0.0076
-4.000 -0.2921 0.00816 0.00230 -0.0324 0.8697 0.0099
-3.750 -0.2654 0.00794 0.00206 -0.0322 0.8594 0.0142
-3.500 -0.2386 0.00774 0.00185 -0.0320 0.8494 0.0248
-3.250 -0.2116 0.00757 0.00168 -0.0318 0.8393 0.0356
-3.000 -0.1845 0.00740 0.00152 -0.0317 0.8293 0.0504
-2.750 -0.1576 0.00720 0.00135 -0.0316 0.8181 0.0752
-2.500 -0.1311 0.00690 0.00120 -0.0314 0.8057 0.1238
-2.250 -0.1043 0.00668 0.00107 -0.0313 0.7939 0.1689
-1.750 -0.0503 0.00626 0.00085 -0.0312 0.7720 0.2621
-1.500 -0.0244 0.00585 0.00072 -0.0311 0.7573 0.3668
-1.250 0.0015 0.00550 0.00064 -0.0309 0.7410 0.4700
-1.000 0.0285 0.00536 0.00059 -0.0308 0.7268 0.5198
-0.750 0.0552 0.00518 0.00058 -0.0306 0.7124 0.5850
-0.500 0.0822 0.00510 0.00057 -0.0304 0.6972 0.6290
-0.250 0.1096 0.00510 0.00056 -0.0303 0.6800 0.6493
0.000 0.1370 0.00513 0.00056 -0.0302 0.6624 0.6656
0.250 0.1644 0.00514 0.00058 -0.0300 0.6471 0.6847
0.500 0.1918 0.00515 0.00060 -0.0299 0.6309 0.7036
0.750 0.2192 0.00517 0.00063 -0.0298 0.6135 0.7227
1.000 0.2464 0.00523 0.00066 -0.0297 0.5912 0.7369
1.250 0.2736 0.00534 0.00070 -0.0295 0.5626 0.7470
1.500 0.3002 0.00551 0.00076 -0.0293 0.5201 0.7573
1.750 0.3266 0.00574 0.00084 -0.0291 0.4699 0.7679
2.000 0.3524 0.00604 0.00095 -0.0289 0.4087 0.7788
2.250 0.3780 0.00638 0.00108 -0.0286 0.3413 0.7904
2.500 0.4040 0.00665 0.00121 -0.0283 0.2921 0.8028
2.750 0.4299 0.00692 0.00138 -0.0281 0.2492 0.8163
3.000 0.4561 0.00711 0.00151 -0.0278 0.2207 0.8310
3.250 0.4819 0.00734 0.00166 -0.0275 0.1860 0.8476
3.500 0.5070 0.00759 0.00183 -0.0271 0.1469 0.8667
3.750 0.5317 0.00778 0.00201 -0.0265 0.1192 0.8943
4.000 0.5572 0.00797 0.00224 -0.0260 0.0900 0.9441
4.250 0.5952 0.00839 0.00252 -0.0286 0.0535 1.0000
4.500 0.6214 0.00867 0.00274 -0.0284 0.0402 1.0000
4.750 0.6473 0.00899 0.00300 -0.0281 0.0261 1.0000
5.000 0.6729 0.00936 0.00329 -0.0278 0.0141 1.0000
5.250 0.6988 0.00968 0.00360 -0.0276 0.0077 1.0000
5.500 0.7245 0.01005 0.00396 -0.0273 0.0046 1.0000
5.750 0.7499 0.01049 0.00447 -0.0269 0.0030 1.0000
6.000 0.7752 0.01097 0.00503 -0.0264 0.0027 1.0000
6.250 0.8005 0.01141 0.00554 -0.0260 0.0026 1.0000
6.500 0.8253 0.01193 0.00615 -0.0256 0.0025 1.0000
6.750 0.8497 0.01254 0.00684 -0.0250 0.0024 1.0000
7.000 0.8737 0.01318 0.00759 -0.0244 0.0023 1.0000
7.250 0.8972 0.01391 0.00841 -0.0238 0.0022 1.0000
7.500 0.9210 0.01455 0.00914 -0.0233 0.0020 1.0000
7.750 0.9450 0.01510 0.00975 -0.0228 0.0018 1.0000
8.000 0.9675 0.01595 0.01075 -0.0221 0.0017 1.0000
8.250 0.9894 0.01689 0.01182 -0.0213 0.0017 1.0000
8.500 1.0114 0.01778 0.01282 -0.0206 0.0016 1.0000
8.750 1.0319 0.01892 0.01412 -0.0197 0.0015 1.0000
9.000 1.0524 0.02001 0.01534 -0.0189 0.0015 1.0000
9.250 1.0723 0.02111 0.01658 -0.0180 0.0014 1.0000
9.500 1.0918 0.02220 0.01781 -0.0171 0.0014 1.0000
9.750 1.1099 0.02344 0.01921 -0.0161 0.0013 1.0000
10.000 1.1259 0.02492 0.02087 -0.0149 0.0012 1.0000
10.250 1.1383 0.02683 0.02300 -0.0134 0.0012 1.0000
10.500 1.1413 0.02983 0.02635 -0.0111 0.0011 1.0000
10.750 1.1440 0.03246 0.02929 -0.0088 0.0011 1.0000
11.000 1.1116 0.03779 0.03507 -0.0034 0.0010 1.0000
11.250 1.1087 0.03963 0.03707 -0.0011 0.0010 1.0000
11.500 1.0791 0.04438 0.04205 0.0008 0.0010 1.0000
11.750 1.0554 0.04958 0.04746 -0.0001 0.0010 1.0000
12.250 1.0289 0.06057 0.05871 -0.0066 0.0010 1.0000
12.500 1.0121 0.06943 0.06771 -0.0136 0.0010 1.0000
12.750 1.0156 0.07437 0.07270 -0.0172 0.0011 1.0000
13.000 0.9969 0.08594 0.08437 -0.0243 0.0011 1.0000
13.250 0.9762 0.09655 0.09503 -0.0297 0.0011 1.0000
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Polar data table (+)
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