NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-209 (naca63209-il) Reynolds number: 500,000 Max Cl/Cd: 78.03 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63209-il-500000.txt Download as CSV file: xf-naca63209-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-209
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4787 0.08191 0.07980 -0.0191 1.0000 0.0206
-9.500 -0.4850 0.07510 0.07300 -0.0227 1.0000 0.0207
-9.250 -0.4955 0.06681 0.06470 -0.0279 1.0000 0.0206
-9.000 -0.5118 0.05985 0.05769 -0.0332 1.0000 0.0206
-8.750 -0.5306 0.05464 0.05241 -0.0368 1.0000 0.0206
-8.500 -0.5510 0.05084 0.04853 -0.0381 1.0000 0.0206
-8.250 -0.5625 0.04664 0.04420 -0.0387 1.0000 0.0206
-6.500 -0.5616 0.02516 0.02059 -0.0357 1.0000 0.0185
-6.250 -0.5471 0.02150 0.01649 -0.0337 1.0000 0.0178
-6.000 -0.5312 0.01942 0.01414 -0.0318 1.0000 0.0180
-5.750 -0.4990 0.01760 0.01207 -0.0329 0.9973 0.0188
-5.500 -0.4623 0.01681 0.01108 -0.0349 0.9938 0.0202
-5.250 -0.4275 0.01561 0.00972 -0.0364 0.9894 0.0208
-5.000 -0.3948 0.01303 0.00700 -0.0379 0.9855 0.0222
-4.750 -0.3587 0.01210 0.00604 -0.0400 0.9820 0.0237
-4.500 -0.3247 0.01158 0.00548 -0.0414 0.9752 0.0264
-4.250 -0.2888 0.01096 0.00480 -0.0433 0.9699 0.0284
-4.000 -0.2574 0.01019 0.00394 -0.0442 0.9605 0.0309
-3.750 -0.2262 0.00962 0.00334 -0.0450 0.9513 0.0363
-3.500 -0.1969 0.00921 0.00286 -0.0453 0.9411 0.0443
-3.250 -0.1704 0.00877 0.00247 -0.0450 0.9290 0.0673
-3.000 -0.1470 0.00744 0.00202 -0.0451 0.9168 0.2917
-2.750 -0.1230 0.00656 0.00184 -0.0448 0.9054 0.4906
-2.500 -0.0971 0.00632 0.00177 -0.0444 0.8947 0.5641
-2.000 -0.0440 0.00614 0.00168 -0.0435 0.8732 0.6379
-1.750 -0.0173 0.00608 0.00167 -0.0431 0.8627 0.6706
-1.500 0.0093 0.00607 0.00167 -0.0427 0.8527 0.7015
-1.250 0.0358 0.00606 0.00169 -0.0421 0.8425 0.7284
-1.000 0.0631 0.00605 0.00168 -0.0419 0.8319 0.7441
-0.750 0.0903 0.00605 0.00166 -0.0416 0.8220 0.7577
-0.500 0.1175 0.00606 0.00164 -0.0413 0.8124 0.7695
-0.250 0.1449 0.00605 0.00164 -0.0411 0.8019 0.7807
0.000 0.1724 0.00606 0.00165 -0.0409 0.7918 0.7919
0.250 0.1998 0.00609 0.00165 -0.0407 0.7821 0.8034
0.500 0.2270 0.00610 0.00167 -0.0405 0.7718 0.8145
0.750 0.2542 0.00611 0.00170 -0.0402 0.7611 0.8254
1.000 0.2812 0.00613 0.00174 -0.0399 0.7506 0.8365
1.250 0.3082 0.00616 0.00178 -0.0396 0.7396 0.8480
1.500 0.3349 0.00620 0.00181 -0.0392 0.7274 0.8600
1.750 0.3611 0.00622 0.00186 -0.0387 0.7134 0.8718
2.000 0.3866 0.00624 0.00189 -0.0380 0.6949 0.8839
2.250 0.4112 0.00628 0.00191 -0.0370 0.6669 0.8967
2.500 0.4354 0.00635 0.00193 -0.0361 0.6403 0.9103
2.750 0.4592 0.00641 0.00198 -0.0350 0.6156 0.9252
3.000 0.4827 0.00647 0.00203 -0.0339 0.5909 0.9421
3.250 0.5076 0.00658 0.00208 -0.0331 0.5519 0.9613
3.500 0.5392 0.00691 0.00216 -0.0341 0.4790 0.9837
3.750 0.5653 0.00783 0.00244 -0.0346 0.3330 1.0000
4.000 0.5854 0.00936 0.00305 -0.0343 0.1361 1.0000
4.250 0.6091 0.01036 0.00363 -0.0341 0.0504 1.0000
4.500 0.6354 0.01092 0.00415 -0.0340 0.0372 1.0000
4.750 0.6610 0.01158 0.00484 -0.0337 0.0307 1.0000
5.000 0.6873 0.01205 0.00533 -0.0336 0.0270 1.0000
5.250 0.7114 0.01289 0.00621 -0.0332 0.0242 1.0000
5.500 0.7336 0.01408 0.00750 -0.0324 0.0228 1.0000
5.750 0.7587 0.01474 0.00823 -0.0320 0.0220 1.0000
6.000 0.7830 0.01561 0.00917 -0.0314 0.0210 1.0000
6.250 0.8077 0.01641 0.01002 -0.0310 0.0198 1.0000
6.500 0.8323 0.01721 0.01088 -0.0306 0.0186 1.0000
6.750 0.8564 0.01827 0.01201 -0.0302 0.0179 1.0000
7.000 0.8800 0.01960 0.01342 -0.0297 0.0173 1.0000
7.250 0.9027 0.02174 0.01569 -0.0290 0.0167 1.0000
7.500 0.9238 0.02502 0.01924 -0.0282 0.0163 1.0000
7.750 0.9439 0.02716 0.02173 -0.0272 0.0156 1.0000
8.000 0.9649 0.02882 0.02366 -0.0263 0.0150 1.0000
8.250 0.9803 0.03227 0.02750 -0.0248 0.0150 1.0000
8.500 0.9899 0.03661 0.03228 -0.0230 0.0152 1.0000
16.000 0.7005 0.19362 0.19184 -0.0820 0.0139 1.0000
16.250 0.7045 0.19719 0.19541 -0.0838 0.0130 1.0000
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Polar data table (+)
Polar graphs
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