NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 500,000 Max Cl/Cd: 67.69 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66209-il-500000.txt Download as CSV file: xf-naca66209-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5050 0.10421 0.10183 -0.0273 1.0000 0.0144
-10.250 -0.5042 0.10002 0.09766 -0.0293 1.0000 0.0152
-8.000 -0.5595 0.06222 0.05979 -0.0447 0.9968 0.0169
-7.750 -0.5463 0.05667 0.05400 -0.0483 0.9913 0.0170
-7.500 -0.5307 0.05153 0.04857 -0.0510 0.9864 0.0170
-7.250 -0.5268 0.04196 0.03872 -0.0548 0.9827 0.0181
-7.000 -0.5068 0.03923 0.03586 -0.0562 0.9779 0.0189
-6.750 -0.4819 0.03717 0.03368 -0.0579 0.9744 0.0206
-6.500 -0.4539 0.03432 0.03053 -0.0591 0.9711 0.0233
-6.250 -0.4215 0.03432 0.03020 -0.0591 0.9672 0.0252
-6.000 -0.4007 0.03158 0.02712 -0.0587 0.9610 0.0253
-5.500 -0.3669 0.02113 0.01585 -0.0566 0.9491 0.0222
-5.250 -0.3426 0.01851 0.01286 -0.0557 0.9444 0.0214
-5.000 -0.3175 0.01709 0.01123 -0.0550 0.9400 0.0222
-4.750 -0.2928 0.01550 0.00944 -0.0541 0.9348 0.0226
-4.500 -0.2672 0.01432 0.00812 -0.0535 0.9307 0.0232
-4.250 -0.2418 0.01349 0.00720 -0.0530 0.9269 0.0241
-4.000 -0.2162 0.01322 0.00685 -0.0525 0.9221 0.0252
-3.750 -0.1947 0.01172 0.00528 -0.0514 0.9178 0.0271
-3.250 -0.1472 0.01056 0.00405 -0.0501 0.9093 0.0319
-3.000 -0.1221 0.01020 0.00364 -0.0496 0.9052 0.0349
-2.750 -0.0968 0.00980 0.00316 -0.0492 0.9019 0.0404
-2.500 -0.0710 0.00951 0.00285 -0.0489 0.8986 0.0484
-2.250 -0.0480 0.00878 0.00254 -0.0484 0.8943 0.1618
-2.000 -0.0380 0.00660 0.00229 -0.0462 0.8897 0.6946
-1.750 -0.0130 0.00655 0.00237 -0.0453 0.8869 0.7619
-1.500 0.0114 0.00664 0.00255 -0.0443 0.8833 0.8002
-1.250 0.0360 0.00677 0.00273 -0.0432 0.8798 0.8248
-1.000 0.0616 0.00687 0.00283 -0.0425 0.8768 0.8390
-0.750 0.0873 0.00696 0.00291 -0.0418 0.8741 0.8509
-0.500 0.1131 0.00706 0.00300 -0.0412 0.8713 0.8617
-0.250 0.1376 0.00717 0.00314 -0.0403 0.8678 0.8710
0.000 0.1647 0.00718 0.00316 -0.0402 0.8645 0.8760
0.250 0.1920 0.00716 0.00313 -0.0401 0.8609 0.8788
0.500 0.2194 0.00716 0.00312 -0.0400 0.8570 0.8819
0.750 0.2464 0.00714 0.00312 -0.0400 0.8517 0.8857
1.000 0.2743 0.00712 0.00309 -0.0401 0.8474 0.8891
1.250 0.3001 0.00702 0.00302 -0.0394 0.8386 0.8918
1.500 0.3256 0.00688 0.00286 -0.0386 0.8258 0.8951
1.750 0.3516 0.00679 0.00275 -0.0380 0.8135 0.8990
2.000 0.3776 0.00670 0.00265 -0.0375 0.7987 0.9030
2.250 0.4017 0.00660 0.00251 -0.0363 0.7755 0.9062
2.500 0.4259 0.00656 0.00247 -0.0353 0.7465 0.9102
2.750 0.4488 0.00663 0.00240 -0.0341 0.6900 0.9149
3.000 0.4523 0.00795 0.00261 -0.0294 0.4302 0.9211
3.250 0.4550 0.00998 0.00325 -0.0255 0.1031 0.9294
3.500 0.4731 0.01061 0.00362 -0.0238 0.0450 0.9350
3.750 0.4955 0.01094 0.00402 -0.0227 0.0380 0.9412
4.000 0.5145 0.01151 0.00464 -0.0210 0.0311 0.9479
4.250 0.5358 0.01187 0.00507 -0.0198 0.0287 0.9556
4.500 0.5580 0.01231 0.00558 -0.0188 0.0267 0.9632
4.750 0.5822 0.01288 0.00620 -0.0182 0.0250 0.9715
5.000 0.6111 0.01364 0.00702 -0.0188 0.0231 0.9777
5.250 0.6398 0.01487 0.00829 -0.0195 0.0219 0.9840
5.500 0.6703 0.01715 0.01067 -0.0204 0.0203 0.9880
5.750 0.7036 0.01816 0.01180 -0.0218 0.0198 0.9936
6.000 0.7355 0.01963 0.01343 -0.0227 0.0193 1.0000
6.250 0.7577 0.02143 0.01544 -0.0217 0.0190 1.0000
6.500 0.7807 0.02404 0.01834 -0.0208 0.0191 1.0000
6.750 0.8035 0.02585 0.02040 -0.0199 0.0182 1.0000
7.750 0.8438 0.04597 0.04193 -0.0119 0.0205 1.0000
8.000 0.8501 0.04950 0.04574 -0.0097 0.0205 1.0000
8.250 0.8535 0.05298 0.04949 -0.0074 0.0204 1.0000
8.500 0.8549 0.05619 0.05295 -0.0051 0.0204 1.0000
8.750 0.8711 0.05650 0.05360 -0.0025 0.0185 1.0000
9.000 0.8710 0.05987 0.05717 -0.0005 0.0171 1.0000
9.250 0.8654 0.06318 0.06062 0.0015 0.0164 1.0000
9.500 0.8510 0.06640 0.06395 0.0043 0.0162 1.0000
9.750 0.8346 0.06970 0.06736 0.0061 0.0160 1.0000
10.000 0.8121 0.07456 0.07233 0.0062 0.0163 1.0000
10.250 0.7927 0.07971 0.07756 0.0044 0.0161 1.0000
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Polar data table (+)
Polar graphs
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