HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 50,000 Max Cl/Cd: 36.99 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2010-il-50000-n5.txt Download as CSV file: xf-hq2010-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4625 0.12338 0.11607 -0.0204 1.0000 0.0534
-10.750 -0.4585 0.11914 0.11186 -0.0216 1.0000 0.0508
-10.500 -0.4571 0.11480 0.10757 -0.0235 1.0000 0.0485
-10.000 -0.4657 0.10413 0.09706 -0.0309 1.0000 0.0433
-9.750 -0.4633 0.10002 0.09300 -0.0321 1.0000 0.0429
-9.500 -0.4623 0.09581 0.08885 -0.0336 1.0000 0.0424
-9.250 -0.4634 0.09136 0.08447 -0.0356 1.0000 0.0421
-9.000 -0.4661 0.08668 0.07988 -0.0380 1.0000 0.0419
-8.750 -0.4704 0.08177 0.07505 -0.0409 1.0000 0.0416
-8.500 -0.4781 0.07685 0.07019 -0.0441 1.0000 0.0412
-8.250 -0.4893 0.07240 0.06581 -0.0463 1.0000 0.0408
-8.000 -0.4991 0.06802 0.06141 -0.0479 1.0000 0.0406
-7.750 -0.5071 0.06391 0.05723 -0.0487 1.0000 0.0404
-7.500 -0.5138 0.05987 0.05305 -0.0489 1.0000 0.0405
-7.250 -0.5175 0.05600 0.04897 -0.0486 1.0000 0.0409
-7.000 -0.5181 0.05225 0.04492 -0.0478 1.0000 0.0417
-6.750 -0.5155 0.04863 0.04090 -0.0468 1.0000 0.0426
-6.500 -0.5094 0.04523 0.03700 -0.0455 1.0000 0.0434
-6.250 -0.5002 0.04195 0.03331 -0.0441 1.0000 0.0441
-6.000 -0.4883 0.03903 0.03014 -0.0428 1.0000 0.0451
-5.750 -0.4740 0.03654 0.02730 -0.0415 1.0000 0.0467
-5.500 -0.4576 0.03434 0.02480 -0.0402 1.0000 0.0489
-5.250 -0.4397 0.03244 0.02250 -0.0389 1.0000 0.0537
-5.000 -0.4206 0.03048 0.02020 -0.0376 1.0000 0.0584
-4.750 -0.4013 0.02888 0.01848 -0.0363 1.0000 0.0633
-4.500 -0.3815 0.02752 0.01690 -0.0350 1.0000 0.0724
-4.250 -0.3617 0.02630 0.01553 -0.0335 1.0000 0.0814
-4.000 -0.3426 0.02526 0.01443 -0.0322 1.0000 0.0951
-3.750 -0.3231 0.02423 0.01329 -0.0309 1.0000 0.1085
-3.500 -0.3027 0.02330 0.01240 -0.0301 1.0000 0.1298
-3.250 -0.2819 0.02233 0.01151 -0.0295 1.0000 0.1597
-3.000 -0.2510 0.02077 0.01061 -0.0315 0.9955 0.2690
-2.750 -0.2275 0.01960 0.01089 -0.0306 0.9889 0.5633
-2.500 -0.2021 0.01975 0.01116 -0.0291 0.9811 0.6798
-2.250 -0.1783 0.01994 0.01132 -0.0270 0.9731 0.7570
-2.000 -0.1582 0.01999 0.01137 -0.0241 0.9647 0.8200
-1.750 -0.1284 0.02001 0.01132 -0.0231 0.9584 0.8761
-1.500 -0.0808 0.02004 0.01117 -0.0262 0.9536 0.9283
-1.250 -0.0207 0.02010 0.01092 -0.0329 0.9495 0.9638
-1.000 0.0344 0.02015 0.01070 -0.0392 0.9446 0.9913
-0.750 0.0633 0.02020 0.01054 -0.0409 0.9349 1.0000
-0.500 0.0934 0.02031 0.01047 -0.0426 0.9261 1.0000
-0.250 0.1265 0.02047 0.01046 -0.0446 0.9178 1.0000
0.000 0.1553 0.02066 0.01049 -0.0458 0.9086 1.0000
0.250 0.1946 0.02085 0.01056 -0.0487 0.9021 1.0000
0.500 0.2241 0.02105 0.01066 -0.0496 0.8914 1.0000
0.750 0.2575 0.02124 0.01076 -0.0511 0.8812 1.0000
1.000 0.2953 0.02137 0.01084 -0.0532 0.8724 1.0000
1.250 0.3264 0.02157 0.01099 -0.0541 0.8619 1.0000
1.500 0.3553 0.02180 0.01121 -0.0546 0.8512 1.0000
1.750 0.3869 0.02197 0.01139 -0.0554 0.8404 1.0000
2.000 0.4200 0.02200 0.01143 -0.0560 0.8272 1.0000
2.250 0.4518 0.02193 0.01138 -0.0562 0.8114 1.0000
2.500 0.4832 0.02181 0.01132 -0.0561 0.7950 1.0000
2.750 0.5135 0.02173 0.01129 -0.0559 0.7795 1.0000
3.000 0.5422 0.02173 0.01135 -0.0556 0.7650 1.0000
3.250 0.5707 0.02171 0.01141 -0.0552 0.7499 1.0000
3.500 0.5993 0.02166 0.01149 -0.0546 0.7343 1.0000
3.750 0.6243 0.02171 0.01164 -0.0537 0.7159 1.0000
4.000 0.6505 0.02170 0.01174 -0.0527 0.6967 1.0000
4.250 0.6786 0.02160 0.01174 -0.0519 0.6769 1.0000
4.500 0.7032 0.02163 0.01193 -0.0507 0.6528 1.0000
4.750 0.7282 0.02164 0.01205 -0.0494 0.6262 1.0000
5.000 0.7534 0.02165 0.01215 -0.0481 0.5961 1.0000
5.250 0.7777 0.02175 0.01229 -0.0467 0.5613 1.0000
5.500 0.8018 0.02191 0.01247 -0.0452 0.5231 1.0000
5.750 0.8236 0.02228 0.01277 -0.0436 0.4805 1.0000
6.000 0.8438 0.02281 0.01318 -0.0420 0.4365 1.0000
6.250 0.8627 0.02353 0.01369 -0.0403 0.3954 1.0000
6.500 0.8802 0.02440 0.01442 -0.0386 0.3557 1.0000
6.750 0.8967 0.02533 0.01526 -0.0371 0.3179 1.0000
7.000 0.9123 0.02636 0.01622 -0.0355 0.2837 1.0000
7.250 0.9275 0.02747 0.01729 -0.0339 0.2493 1.0000
7.500 0.9417 0.02865 0.01843 -0.0323 0.2164 1.0000
7.750 0.9556 0.02991 0.01966 -0.0308 0.1846 1.0000
8.000 0.9697 0.03132 0.02101 -0.0292 0.1591 1.0000
8.250 0.9842 0.03280 0.02248 -0.0278 0.1370 1.0000
8.500 0.9979 0.03435 0.02396 -0.0264 0.1205 1.0000
8.750 1.0156 0.03602 0.02580 -0.0253 0.1088 1.0000
9.000 1.0354 0.03783 0.02776 -0.0243 0.0995 1.0000
9.250 1.0518 0.03964 0.02964 -0.0232 0.0908 1.0000
9.500 1.0675 0.04150 0.03168 -0.0221 0.0827 1.0000
9.750 1.0886 0.04402 0.03446 -0.0213 0.0770 1.0000
10.000 1.1019 0.04636 0.03705 -0.0200 0.0707 1.0000
10.250 1.1097 0.04891 0.03984 -0.0185 0.0644 1.0000
10.500 1.1160 0.05199 0.04330 -0.0167 0.0596 1.0000
10.750 1.1174 0.05443 0.04572 -0.0150 0.0545 1.0000
11.000 1.1065 0.05729 0.04904 -0.0126 0.0504 1.0000
11.250 1.0993 0.05962 0.05149 -0.0113 0.0461 1.0000
11.500 1.0931 0.06257 0.05445 -0.0105 0.0428 1.0000
11.750 1.0785 0.06692 0.05922 -0.0102 0.0412 1.0000
12.000 1.0624 0.07178 0.06441 -0.0107 0.0400 1.0000
12.250 1.0458 0.07720 0.07010 -0.0122 0.0396 1.0000
12.500 1.0259 0.08347 0.07661 -0.0148 0.0394 1.0000
12.750 1.0051 0.09065 0.08399 -0.0184 0.0401 1.0000
13.000 0.9837 0.09874 0.09223 -0.0231 0.0411 1.0000
13.250 0.9633 0.10748 0.10109 -0.0283 0.0420 1.0000
13.500 0.9467 0.11612 0.10979 -0.0333 0.0429 1.0000
13.750 0.9300 0.12550 0.11919 -0.0388 0.0434 1.0000
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Polar data table (+)
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