HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: HQ 2.0/8 AIRFOIL (hq208-il) Reynolds number: 200,000 Max Cl/Cd: 74.61 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq208-il-200000.txt Download as CSV file: xf-hq208-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3766 0.09623 0.09289 -0.0218 1.0000 0.0334
-9.250 -0.3738 0.09250 0.08918 -0.0226 1.0000 0.0343
-9.000 -0.4635 0.09607 0.09258 -0.0247 1.0000 0.0316
-8.750 -0.4575 0.09283 0.08936 -0.0244 1.0000 0.0324
-8.500 -0.4532 0.08964 0.08618 -0.0249 1.0000 0.0332
-8.250 -0.4507 0.08629 0.08288 -0.0259 1.0000 0.0342
-8.000 -0.4501 0.08289 0.07953 -0.0272 1.0000 0.0352
-7.750 -0.4518 0.07950 0.07618 -0.0287 1.0000 0.0359
-7.500 -0.4561 0.07601 0.07276 -0.0305 1.0000 0.0364
-7.250 -0.4567 0.07152 0.06831 -0.0349 1.0000 0.0371
-7.000 -0.4557 0.06702 0.06381 -0.0388 1.0000 0.0379
-6.750 -0.4539 0.06258 0.05932 -0.0416 1.0000 0.0392
-6.500 -0.4489 0.05844 0.05496 -0.0446 1.0000 0.0416
-6.250 -0.4439 0.05648 0.05263 -0.0448 1.0000 0.0426
-6.000 -0.4440 0.05200 0.04795 -0.0440 1.0000 0.0431
-5.750 -0.4419 0.04682 0.04288 -0.0430 1.0000 0.0444
-5.500 -0.4347 0.04415 0.04022 -0.0415 1.0000 0.0459
-5.250 -0.4249 0.04166 0.03763 -0.0404 1.0000 0.0479
-5.000 -0.4117 0.03902 0.03475 -0.0396 1.0000 0.0518
-4.750 -0.3962 0.03567 0.03089 -0.0393 1.0000 0.0576
-4.500 -0.3807 0.03308 0.02823 -0.0386 1.0000 0.0601
-4.250 -0.3495 0.03032 0.02510 -0.0407 0.9974 0.0723
-4.000 -0.3069 0.02398 0.01781 -0.0408 0.9953 0.0385
-3.750 -0.2670 0.02143 0.01452 -0.0414 0.9923 0.0306
-3.500 -0.2324 0.01871 0.01147 -0.0426 0.9891 0.0298
-3.250 -0.1959 0.01707 0.00959 -0.0440 0.9856 0.0303
-3.000 -0.1605 0.01493 0.00740 -0.0455 0.9830 0.0336
-2.750 -0.1256 0.01406 0.00652 -0.0471 0.9782 0.0453
-2.500 -0.0899 0.01278 0.00535 -0.0488 0.9734 0.0953
-2.000 -0.0310 0.01034 0.00531 -0.0503 0.9635 0.7122
-1.750 0.0035 0.01027 0.00526 -0.0513 0.9579 0.7625
-1.500 0.0372 0.01019 0.00522 -0.0520 0.9528 0.8076
-1.250 0.0667 0.01006 0.00511 -0.0517 0.9458 0.8481
-1.000 0.1008 0.00986 0.00501 -0.0519 0.9422 0.9037
-0.750 0.1466 0.00974 0.00489 -0.0549 0.9384 0.9515
-0.500 0.2008 0.00960 0.00466 -0.0604 0.9347 0.9777
-0.250 0.2553 0.00940 0.00438 -0.0660 0.9308 0.9985
0.000 0.2884 0.00924 0.00414 -0.0673 0.9200 1.0000
0.250 0.3193 0.00909 0.00392 -0.0678 0.9086 1.0000
0.500 0.3484 0.00899 0.00375 -0.0678 0.8974 1.0000
0.750 0.3759 0.00892 0.00361 -0.0674 0.8856 1.0000
1.000 0.4023 0.00889 0.00352 -0.0668 0.8738 1.0000
1.250 0.4278 0.00892 0.00352 -0.0662 0.8618 1.0000
1.500 0.4535 0.00895 0.00355 -0.0655 0.8497 1.0000
1.750 0.4793 0.00898 0.00356 -0.0648 0.8373 1.0000
2.000 0.5051 0.00902 0.00358 -0.0642 0.8243 1.0000
2.250 0.5310 0.00904 0.00360 -0.0635 0.8106 1.0000
2.500 0.5568 0.00906 0.00362 -0.0627 0.7958 1.0000
2.750 0.5827 0.00908 0.00367 -0.0620 0.7800 1.0000
3.000 0.6083 0.00912 0.00371 -0.0612 0.7617 1.0000
3.250 0.6338 0.00915 0.00375 -0.0603 0.7407 1.0000
3.500 0.6590 0.00921 0.00380 -0.0594 0.7155 1.0000
3.750 0.6835 0.00930 0.00383 -0.0583 0.6815 1.0000
4.000 0.7066 0.00947 0.00389 -0.0569 0.6308 1.0000
4.250 0.7287 0.00980 0.00399 -0.0555 0.5643 1.0000
4.500 0.7497 0.01033 0.00420 -0.0540 0.4869 1.0000
4.750 0.7700 0.01103 0.00455 -0.0527 0.4109 1.0000
5.000 0.7905 0.01178 0.00499 -0.0516 0.3416 1.0000
5.250 0.8117 0.01251 0.00553 -0.0507 0.2864 1.0000
5.500 0.8337 0.01321 0.00607 -0.0499 0.2397 1.0000
5.750 0.8537 0.01420 0.00669 -0.0489 0.1557 1.0000
6.000 0.8705 0.01577 0.00777 -0.0474 0.0916 1.0000
6.250 0.8914 0.01674 0.00870 -0.0464 0.0721 1.0000
6.500 0.9136 0.01748 0.00941 -0.0458 0.0566 1.0000
6.750 0.9349 0.01839 0.01039 -0.0449 0.0459 1.0000
7.000 0.9522 0.01999 0.01199 -0.0433 0.0298 1.0000
7.250 0.9704 0.02173 0.01391 -0.0416 0.0228 1.0000
7.500 0.9884 0.02367 0.01592 -0.0401 0.0201 1.0000
7.750 1.0064 0.02759 0.02005 -0.0385 0.0187 1.0000
8.000 1.0273 0.03002 0.02279 -0.0373 0.0183 1.0000
8.250 1.0469 0.03179 0.02490 -0.0359 0.0170 1.0000
8.500 1.0646 0.03354 0.02695 -0.0346 0.0151 1.0000
8.750 1.0780 0.03651 0.03031 -0.0328 0.0144 1.0000
9.000 1.0856 0.04045 0.03474 -0.0304 0.0144 1.0000
9.250 1.0863 0.04494 0.03974 -0.0277 0.0146 1.0000
9.500 1.0809 0.04958 0.04482 -0.0249 0.0150 1.0000
9.750 1.0697 0.05402 0.04963 -0.0221 0.0154 1.0000
10.000 1.0532 0.05777 0.05363 -0.0190 0.0157 1.0000
10.250 1.0338 0.06163 0.05771 -0.0169 0.0159 1.0000
10.500 1.0144 0.06585 0.06212 -0.0164 0.0161 1.0000
10.750 0.9932 0.07096 0.06740 -0.0177 0.0162 1.0000
11.000 0.9736 0.07670 0.07329 -0.0206 0.0165 1.0000
11.250 0.9527 0.08394 0.08067 -0.0257 0.0165 1.0000
11.500 0.9322 0.09304 0.08988 -0.0327 0.0167 1.0000
11.750 0.9125 0.10447 0.10136 -0.0409 0.0170 1.0000
12.000 0.8979 0.11464 0.11151 -0.0467 0.0177 1.0000
12.250 0.8857 0.12383 0.12067 -0.0513 0.0182 1.0000
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