ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA HOR04 AIRFOIL (hor04-il) Reynolds number: 50,000 Max Cl/Cd: 32.31 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor04-il-50000-n5.txt Download as CSV file: xf-hor04-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA HOR04 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6282 0.11605 0.10923 0.0254 1.0000 0.0788
-8.250 -0.6284 0.11322 0.10648 0.0218 1.0000 0.0819
-8.000 -0.6299 0.11082 0.10416 0.0149 1.0000 0.0832
-7.750 -0.6215 0.10554 0.09893 0.0153 1.0000 0.0849
-7.500 -0.6113 0.10113 0.09451 0.0167 1.0000 0.0888
-7.250 -0.6034 0.09732 0.09072 0.0127 1.0000 0.0937
-6.750 -0.5830 0.08869 0.08213 0.0056 1.0000 0.1019
-6.500 -0.5651 0.08448 0.07780 -0.0072 1.0000 0.1112
-6.250 -0.5558 0.08037 0.07368 -0.0031 1.0000 0.1217
-6.000 -0.5364 0.07613 0.06930 -0.0122 1.0000 0.1383
-5.500 -0.5103 0.06819 0.06146 -0.0103 1.0000 0.1711
-5.250 -0.4925 0.06429 0.05751 -0.0129 1.0000 0.1958
-4.750 -0.3939 0.04940 0.04133 -0.0320 1.0000 0.0643
-4.500 -0.3579 0.04473 0.03607 -0.0353 1.0000 0.0534
-4.250 -0.3274 0.04076 0.03174 -0.0375 1.0000 0.0502
-4.000 -0.2942 0.03710 0.02755 -0.0395 1.0000 0.0474
-3.750 -0.2602 0.03388 0.02369 -0.0409 1.0000 0.0452
-3.500 -0.2270 0.03129 0.02038 -0.0418 1.0000 0.0439
-3.250 -0.1961 0.02900 0.01764 -0.0422 1.0000 0.0436
-3.000 -0.1669 0.02675 0.01513 -0.0427 1.0000 0.0453
-2.750 -0.1382 0.02508 0.01326 -0.0429 1.0000 0.0503
-2.500 -0.1094 0.02357 0.01142 -0.0425 1.0000 0.0540
-2.250 -0.0815 0.02217 0.00975 -0.0418 1.0000 0.0559
-2.000 -0.0546 0.02065 0.00811 -0.0412 1.0000 0.0600
-1.750 -0.0266 0.01958 0.00694 -0.0412 1.0000 0.0740
-1.500 0.0024 0.01857 0.00578 -0.0412 1.0000 0.0851
-1.250 0.0319 0.01757 0.00481 -0.0415 1.0000 0.1113
-1.000 0.0451 0.01377 0.00409 -0.0379 1.0000 1.0000
-0.750 0.0730 0.01379 0.00361 -0.0377 1.0000 1.0000
-0.500 0.1005 0.01381 0.00330 -0.0376 1.0000 1.0000
-0.250 0.1277 0.01385 0.00312 -0.0375 1.0000 1.0000
0.000 0.1547 0.01391 0.00303 -0.0375 1.0000 1.0000
0.250 0.1814 0.01398 0.00301 -0.0374 1.0000 1.0000
0.500 0.2078 0.01407 0.00306 -0.0372 1.0000 1.0000
0.750 0.2340 0.01418 0.00317 -0.0371 1.0000 1.0000
1.000 0.2598 0.01431 0.00333 -0.0369 1.0000 1.0000
1.250 0.2853 0.01446 0.00355 -0.0368 1.0000 1.0000
1.500 0.3105 0.01465 0.00384 -0.0366 1.0000 1.0000
1.750 0.3353 0.01487 0.00421 -0.0364 1.0000 1.0000
2.000 0.3598 0.01514 0.00472 -0.0362 1.0000 1.0000
2.250 0.3839 0.01546 0.00525 -0.0361 1.0000 1.0000
2.500 0.4077 0.01586 0.00590 -0.0361 1.0000 1.0000
2.750 0.4633 0.01604 0.00652 -0.0420 0.9679 1.0000
3.000 0.5205 0.01611 0.00622 -0.0423 0.6911 1.0000
3.250 0.5361 0.01737 0.00648 -0.0379 0.4486 1.0000
3.500 0.5553 0.02044 0.00754 -0.0374 0.1398 1.0000
3.750 0.5816 0.02191 0.00892 -0.0372 0.1110 1.0000
4.000 0.6082 0.02330 0.01041 -0.0369 0.0977 1.0000
4.250 0.6343 0.02466 0.01188 -0.0366 0.0826 1.0000
4.500 0.6599 0.02634 0.01361 -0.0359 0.0748 1.0000
4.750 0.6872 0.02828 0.01598 -0.0349 0.0700 1.0000
5.000 0.7143 0.03042 0.01834 -0.0343 0.0636 1.0000
5.250 0.7411 0.03278 0.02112 -0.0339 0.0556 1.0000
5.500 0.7682 0.03573 0.02456 -0.0334 0.0524 1.0000
5.750 0.7927 0.03897 0.02806 -0.0333 0.0491 1.0000
6.000 0.8174 0.04254 0.03248 -0.0330 0.0445 1.0000
6.250 0.8397 0.04657 0.03717 -0.0329 0.0420 1.0000
6.500 0.8594 0.05123 0.04245 -0.0329 0.0414 1.0000
6.750 0.8760 0.05633 0.04822 -0.0332 0.0413 1.0000
7.000 0.8890 0.06182 0.05422 -0.0340 0.0416 1.0000
7.250 0.8984 0.06757 0.06039 -0.0351 0.0422 1.0000
7.500 0.9042 0.07344 0.06658 -0.0367 0.0430 1.0000
7.750 0.9069 0.07933 0.07269 -0.0387 0.0438 1.0000
8.000 0.9071 0.08516 0.07868 -0.0411 0.0447 1.0000
8.250 0.9056 0.09091 0.08452 -0.0438 0.0455 1.0000
8.500 0.9032 0.09657 0.09023 -0.0467 0.0462 1.0000
8.750 0.8993 0.10203 0.09569 -0.0495 0.0468 1.0000
9.000 0.8975 0.10762 0.10125 -0.0526 0.0474 1.0000
9.250 0.8973 0.11299 0.10660 -0.0548 0.0478 1.0000
9.500 0.8979 0.11833 0.11193 -0.0566 0.0481 1.0000
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Polar data table (+)
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