NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-35 (naca001035-il) Reynolds number: 200,000 Max Cl/Cd: 37.42 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001035-il-200000.txt Download as CSV file: xf-naca001035-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-35
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4994 0.08976 0.08642 -0.0396 1.0000 0.0419
-10.000 -0.5131 0.08395 0.08064 -0.0424 1.0000 0.0419
-9.750 -0.5294 0.07834 0.07502 -0.0445 1.0000 0.0417
-9.500 -0.5479 0.07357 0.07024 -0.0451 1.0000 0.0414
-9.250 -0.5691 0.06943 0.06608 -0.0443 1.0000 0.0411
-9.000 -0.5919 0.06597 0.06259 -0.0419 1.0000 0.0408
-8.750 -0.6162 0.06318 0.05977 -0.0379 1.0000 0.0406
-8.500 -0.6415 0.06101 0.05757 -0.0323 1.0000 0.0405
-8.250 -0.6631 0.05856 0.05505 -0.0271 1.0000 0.0407
-8.000 -0.6818 0.05608 0.05243 -0.0219 1.0000 0.0414
-7.750 -0.7016 0.05500 0.05106 -0.0154 1.0000 0.0426
-7.500 -0.7136 0.05383 0.04961 -0.0097 1.0000 0.0430
-7.250 -0.7218 0.05163 0.04717 -0.0048 1.0000 0.0432
-7.000 -0.7702 0.05688 0.05180 0.0020 1.0000 0.0436
-6.750 -0.7696 0.05052 0.04551 0.0039 1.0000 0.0451
-6.500 -0.7637 0.04768 0.04264 0.0065 1.0000 0.0467
-6.250 -0.7577 0.04529 0.04011 0.0096 1.0000 0.0490
-6.000 -0.7505 0.04727 0.04140 0.0153 1.0000 0.0558
-5.750 -0.7474 0.04043 0.03454 0.0174 1.0000 0.0583
-5.500 -0.7351 0.03798 0.03205 0.0194 1.0000 0.0616
-5.250 -0.7267 0.03619 0.02983 0.0230 1.0000 0.0713
-5.000 -0.7112 0.03385 0.02742 0.0247 1.0000 0.0764
-4.750 -0.6787 0.02803 0.02057 0.0291 1.0000 0.0378
-4.500 -0.6543 0.02535 0.01744 0.0309 1.0000 0.0355
-4.250 -0.6293 0.02344 0.01522 0.0322 1.0000 0.0356
-4.000 -0.6018 0.02152 0.01300 0.0331 1.0000 0.0340
-3.750 -0.5773 0.02010 0.01147 0.0341 1.0000 0.0349
-3.500 -0.5552 0.01898 0.01030 0.0354 1.0000 0.0369
-3.250 -0.5345 0.01832 0.00957 0.0367 1.0000 0.0418
-3.000 -0.5159 0.01719 0.00838 0.0386 1.0000 0.0455
-2.750 -0.4972 0.01643 0.00761 0.0402 1.0000 0.0520
-2.500 -0.4776 0.01581 0.00695 0.0417 1.0000 0.0672
-2.250 -0.4725 0.01265 0.00605 0.0452 1.0000 0.5224
-2.000 -0.2298 0.01702 0.01144 0.0091 1.0000 0.9738
-1.750 -0.1802 0.01712 0.01140 0.0040 1.0000 0.9830
-1.500 -0.1373 0.01699 0.01114 0.0000 1.0000 0.9872
-1.250 -0.0977 0.01692 0.01099 -0.0034 1.0000 0.9928
-1.000 -0.0552 0.01681 0.01083 -0.0073 1.0000 0.9974
-0.750 -0.0266 0.01673 0.01071 -0.0085 1.0000 1.0000
-0.500 -0.0177 0.01667 0.01064 -0.0057 1.0000 1.0000
-0.250 -0.0089 0.01664 0.01060 -0.0029 1.0000 1.0000
0.000 0.0000 0.01663 0.01058 0.0000 1.0000 1.0000
0.250 0.0089 0.01664 0.01060 0.0029 1.0000 1.0000
0.500 0.0177 0.01667 0.01064 0.0057 1.0000 1.0000
0.750 0.0266 0.01672 0.01070 0.0085 1.0000 1.0000
1.000 0.0552 0.01680 0.01082 0.0073 0.9974 1.0000
1.250 0.0977 0.01691 0.01099 0.0034 0.9928 1.0000
1.500 0.1372 0.01698 0.01114 0.0000 0.9872 1.0000
1.750 0.1801 0.01712 0.01140 -0.0040 0.9830 1.0000
2.000 0.2305 0.01701 0.01143 -0.0092 0.9737 1.0000
2.250 0.4726 0.01263 0.00605 -0.0452 0.5262 1.0000
2.500 0.4776 0.01580 0.00695 -0.0417 0.0673 1.0000
2.750 0.4972 0.01643 0.00760 -0.0402 0.0521 1.0000
3.000 0.5159 0.01719 0.00837 -0.0386 0.0455 1.0000
3.250 0.5345 0.01831 0.00956 -0.0367 0.0418 1.0000
3.500 0.5552 0.01898 0.01029 -0.0354 0.0369 1.0000
3.750 0.5773 0.02010 0.01147 -0.0341 0.0348 1.0000
4.000 0.6017 0.02151 0.01299 -0.0331 0.0340 1.0000
4.250 0.6292 0.02344 0.01521 -0.0322 0.0356 1.0000
4.500 0.6543 0.02536 0.01746 -0.0309 0.0356 1.0000
4.750 0.6786 0.02802 0.02056 -0.0291 0.0378 1.0000
5.000 0.6927 0.02149 0.01556 -0.0229 0.0754 1.0000
5.250 0.7067 0.02421 0.01832 -0.0213 0.0710 1.0000
5.500 0.7120 0.02608 0.02064 -0.0173 0.0617 1.0000
5.750 0.7224 0.02867 0.02327 -0.0151 0.0583 1.0000
7.000 0.7702 0.05685 0.05177 -0.0020 0.0436 1.0000
7.250 0.7217 0.05153 0.04707 0.0048 0.0432 1.0000
7.500 0.7135 0.05375 0.04953 0.0097 0.0430 1.0000
7.750 0.7011 0.05485 0.05091 0.0155 0.0425 1.0000
8.000 0.6817 0.05598 0.05233 0.0219 0.0414 1.0000
8.250 0.6630 0.05843 0.05492 0.0270 0.0407 1.0000
8.500 0.6413 0.06088 0.05744 0.0323 0.0405 1.0000
8.750 0.6161 0.06306 0.05964 0.0379 0.0406 1.0000
9.000 0.5918 0.06584 0.06246 0.0419 0.0408 1.0000
9.250 0.5688 0.06931 0.06596 0.0443 0.0411 1.0000
9.500 0.5482 0.07339 0.07007 0.0452 0.0414 1.0000
9.750 0.5292 0.07822 0.07490 0.0445 0.0417 1.0000
10.000 0.5128 0.08381 0.08050 0.0424 0.0419 1.0000
10.250 0.4989 0.08965 0.08631 0.0395 0.0419 1.0000
10.500 0.4871 0.09498 0.09160 0.0372 0.0415 1.0000
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Polar data table (+)
Polar graphs
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