NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA-0009 9.0% smoothed (n0009sm-il) Reynolds number: 100,000 Max Cl/Cd: 33.45 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0009sm-il-100000-n5.txt Download as CSV file: xf-n0009sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA-0009 9.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7125 0.09267 0.08756 -0.0119 1.0000 0.0297
-11.250 -0.7440 0.07951 0.07448 -0.0205 1.0000 0.0288
-11.000 -0.7809 0.06808 0.06296 -0.0297 1.0000 0.0275
-10.750 -0.8254 0.05924 0.05387 -0.0344 1.0000 0.0259
-10.500 -0.8507 0.05479 0.04921 -0.0336 1.0000 0.0257
-10.250 -0.8652 0.05197 0.04621 -0.0310 1.0000 0.0263
-10.000 -0.8747 0.04890 0.04288 -0.0287 1.0000 0.0272
-9.750 -0.8815 0.04554 0.03916 -0.0263 1.0000 0.0283
-9.500 -0.8849 0.04194 0.03511 -0.0236 1.0000 0.0295
-9.250 -0.8832 0.03854 0.03117 -0.0210 1.0000 0.0310
-9.000 -0.8757 0.03585 0.02809 -0.0188 1.0000 0.0329
-8.750 -0.8615 0.03486 0.02708 -0.0174 1.0000 0.0355
-8.500 -0.8476 0.03329 0.02519 -0.0156 1.0000 0.0387
-8.250 -0.8326 0.03132 0.02277 -0.0137 1.0000 0.0418
-8.000 -0.8166 0.02976 0.02108 -0.0122 1.0000 0.0453
-7.750 -0.7986 0.02856 0.01975 -0.0109 1.0000 0.0486
-7.500 -0.7796 0.02721 0.01813 -0.0094 1.0000 0.0524
-7.250 -0.7603 0.02589 0.01658 -0.0080 1.0000 0.0564
-7.000 -0.7408 0.02473 0.01541 -0.0067 1.0000 0.0598
-6.750 -0.7206 0.02363 0.01418 -0.0054 1.0000 0.0633
-6.500 -0.6996 0.02278 0.01305 -0.0040 1.0000 0.0678
-6.250 -0.6809 0.02173 0.01208 -0.0026 1.0000 0.0727
-6.000 -0.6609 0.02089 0.01115 -0.0012 1.0000 0.0775
-5.750 -0.6414 0.02004 0.01022 0.0004 1.0000 0.0822
-5.500 -0.6224 0.01926 0.00945 0.0019 1.0000 0.0884
-5.250 -0.6028 0.01857 0.00875 0.0034 1.0000 0.0974
-5.000 -0.5831 0.01793 0.00804 0.0049 1.0000 0.1082
-4.750 -0.5637 0.01724 0.00740 0.0064 1.0000 0.1216
-4.500 -0.5446 0.01655 0.00683 0.0079 1.0000 0.1423
-4.250 -0.5255 0.01585 0.00634 0.0094 1.0000 0.1806
-4.000 -0.5068 0.01517 0.00592 0.0109 1.0000 0.2358
-3.750 -0.4878 0.01458 0.00556 0.0124 1.0000 0.2942
-3.500 -0.4689 0.01405 0.00530 0.0140 1.0000 0.3585
-3.250 -0.4500 0.01359 0.00509 0.0157 1.0000 0.4214
-3.000 -0.4309 0.01318 0.00493 0.0175 1.0000 0.4836
-2.750 -0.4117 0.01281 0.00482 0.0193 1.0000 0.5471
-2.500 -0.3920 0.01248 0.00475 0.0212 1.0000 0.6170
-2.250 -0.3704 0.01222 0.00477 0.0230 1.0000 0.6883
-2.000 -0.3453 0.01208 0.00484 0.0241 1.0000 0.7529
-1.750 -0.3157 0.01206 0.00494 0.0243 1.0000 0.8064
-1.500 -0.2796 0.01213 0.00504 0.0231 1.0000 0.8537
-1.250 -0.2360 0.01228 0.00518 0.0203 1.0000 0.8919
-1.000 -0.1912 0.01243 0.00530 0.0171 1.0000 0.9223
-0.750 -0.1454 0.01257 0.00537 0.0134 1.0000 0.9457
-0.500 -0.1009 0.01269 0.00546 0.0099 1.0000 0.9657
-0.250 -0.0562 0.01279 0.00553 0.0061 1.0000 0.9828
0.000 0.0000 0.01279 0.00552 0.0000 0.9912 0.9912
0.250 0.0560 0.01279 0.00553 -0.0061 0.9828 1.0000
0.500 0.1010 0.01269 0.00546 -0.0099 0.9656 1.0000
0.750 0.1454 0.01257 0.00537 -0.0134 0.9457 1.0000
1.000 0.1912 0.01243 0.00529 -0.0171 0.9222 1.0000
1.250 0.2360 0.01228 0.00518 -0.0203 0.8919 1.0000
1.500 0.2796 0.01213 0.00504 -0.0231 0.8536 1.0000
1.750 0.3156 0.01206 0.00494 -0.0243 0.8063 1.0000
2.000 0.3452 0.01208 0.00484 -0.0241 0.7528 1.0000
2.250 0.3703 0.01222 0.00477 -0.0229 0.6882 1.0000
2.500 0.3919 0.01248 0.00475 -0.0212 0.6171 1.0000
2.750 0.4115 0.01281 0.00481 -0.0193 0.5466 1.0000
3.000 0.4308 0.01318 0.00492 -0.0175 0.4835 1.0000
3.250 0.4499 0.01359 0.00508 -0.0157 0.4208 1.0000
3.500 0.4688 0.01405 0.00529 -0.0140 0.3584 1.0000
3.750 0.4877 0.01458 0.00556 -0.0124 0.2947 1.0000
4.000 0.5067 0.01517 0.00592 -0.0109 0.2354 1.0000
4.250 0.5254 0.01585 0.00633 -0.0094 0.1806 1.0000
4.500 0.5444 0.01655 0.00682 -0.0079 0.1422 1.0000
4.750 0.5636 0.01724 0.00739 -0.0064 0.1214 1.0000
5.000 0.5830 0.01793 0.00804 -0.0048 0.1081 1.0000
5.250 0.6028 0.01857 0.00874 -0.0034 0.0973 1.0000
5.500 0.6223 0.01926 0.00945 -0.0019 0.0884 1.0000
5.750 0.6413 0.02004 0.01022 -0.0003 0.0822 1.0000
6.000 0.6609 0.02089 0.01115 0.0012 0.0774 1.0000
6.250 0.6809 0.02174 0.01208 0.0027 0.0727 1.0000
6.500 0.6996 0.02279 0.01305 0.0041 0.0678 1.0000
6.750 0.7205 0.02363 0.01418 0.0054 0.0633 1.0000
7.000 0.7408 0.02473 0.01541 0.0067 0.0598 1.0000
7.250 0.7603 0.02590 0.01659 0.0080 0.0564 1.0000
7.500 0.7796 0.02722 0.01813 0.0094 0.0525 1.0000
7.750 0.7987 0.02857 0.01976 0.0109 0.0487 1.0000
8.000 0.8166 0.02973 0.02103 0.0122 0.0452 1.0000
8.250 0.8327 0.03132 0.02276 0.0137 0.0419 1.0000
8.500 0.8477 0.03329 0.02519 0.0156 0.0387 1.0000
8.750 0.8616 0.03483 0.02705 0.0173 0.0355 1.0000
9.000 0.8759 0.03580 0.02803 0.0187 0.0328 1.0000
9.250 0.8834 0.03854 0.03116 0.0209 0.0310 1.0000
9.500 0.8850 0.04198 0.03515 0.0236 0.0295 1.0000
9.750 0.8815 0.04556 0.03919 0.0262 0.0283 1.0000
10.000 0.8746 0.04899 0.04297 0.0287 0.0273 1.0000
10.250 0.8654 0.05203 0.04626 0.0310 0.0264 1.0000
10.500 0.8509 0.05484 0.04925 0.0335 0.0257 1.0000
10.750 0.8258 0.05927 0.05390 0.0343 0.0258 1.0000
11.000 0.7829 0.06785 0.06273 0.0297 0.0273 1.0000
11.250 0.7449 0.07951 0.07449 0.0203 0.0288 1.0000
11.500 0.7128 0.09289 0.08778 0.0116 0.0297 1.0000
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Polar data table (+)
Polar graphs
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