NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63-209 (naca63209-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.66 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63209-il-1000000-n5.txt Download as CSV file: xf-naca63209-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.9033 0.05353 0.05185 -0.0385 1.0000 0.0037
-12.250 -0.9821 0.04018 0.03808 -0.0448 1.0000 0.0035
-12.000 -1.0167 0.03469 0.03224 -0.0428 1.0000 0.0035
-11.750 -1.0164 0.03167 0.02897 -0.0419 1.0000 0.0036
-11.500 -1.0166 0.02807 0.02500 -0.0408 1.0000 0.0036
-11.250 -1.0046 0.02597 0.02266 -0.0401 1.0000 0.0037
-11.000 -0.9895 0.02421 0.02069 -0.0394 1.0000 0.0038
-10.750 -0.9725 0.02260 0.01886 -0.0389 1.0000 0.0039
-10.500 -0.9535 0.02127 0.01735 -0.0384 1.0000 0.0039
-10.250 -0.9350 0.01972 0.01559 -0.0378 1.0000 0.0041
-10.000 -0.9151 0.01834 0.01401 -0.0373 1.0000 0.0043
-9.750 -0.8925 0.01754 0.01311 -0.0370 1.0000 0.0046
-9.500 -0.8689 0.01692 0.01242 -0.0367 1.0000 0.0048
-9.250 -0.8452 0.01628 0.01171 -0.0364 1.0000 0.0050
-9.000 -0.8212 0.01571 0.01106 -0.0361 1.0000 0.0052
-8.750 -0.7973 0.01511 0.01038 -0.0357 1.0000 0.0055
-8.500 -0.7733 0.01452 0.00971 -0.0354 1.0000 0.0058
-8.250 -0.7490 0.01404 0.00916 -0.0350 1.0000 0.0061
-8.000 -0.7216 0.01357 0.00860 -0.0353 0.9973 0.0064
-7.750 -0.6907 0.01279 0.00774 -0.0365 0.9886 0.0069
-7.500 -0.6580 0.01238 0.00729 -0.0379 0.9794 0.0074
-7.250 -0.6252 0.01197 0.00685 -0.0393 0.9690 0.0079
-7.000 -0.5937 0.01157 0.00639 -0.0404 0.9563 0.0085
-6.750 -0.5652 0.01122 0.00594 -0.0407 0.9415 0.0090
-6.500 -0.5388 0.01091 0.00555 -0.0405 0.9264 0.0094
-6.250 -0.5126 0.01070 0.00526 -0.0403 0.9127 0.0096
-6.000 -0.4875 0.01014 0.00459 -0.0399 0.8998 0.0107
-5.750 -0.4612 0.00986 0.00426 -0.0397 0.8880 0.0115
-5.500 -0.4347 0.00961 0.00394 -0.0395 0.8765 0.0121
-5.250 -0.4080 0.00937 0.00363 -0.0394 0.8654 0.0128
-5.000 -0.3809 0.00917 0.00337 -0.0393 0.8541 0.0136
-4.750 -0.3537 0.00898 0.00312 -0.0392 0.8435 0.0141
-4.500 -0.3266 0.00874 0.00279 -0.0392 0.8331 0.0146
-4.000 -0.2718 0.00828 0.00222 -0.0391 0.8125 0.0181
-3.750 -0.2441 0.00814 0.00204 -0.0391 0.8028 0.0203
-3.500 -0.2164 0.00800 0.00185 -0.0391 0.7930 0.0232
-3.250 -0.1886 0.00784 0.00168 -0.0392 0.7831 0.0283
-3.000 -0.1607 0.00773 0.00153 -0.0392 0.7736 0.0326
-2.750 -0.1328 0.00760 0.00139 -0.0393 0.7642 0.0417
-2.500 -0.1050 0.00741 0.00126 -0.0394 0.7544 0.0656
-2.250 -0.0772 0.00714 0.00112 -0.0395 0.7452 0.1122
-2.000 -0.0499 0.00664 0.00095 -0.0398 0.7361 0.2189
-1.750 -0.0224 0.00615 0.00080 -0.0402 0.7266 0.3311
-1.500 0.0053 0.00578 0.00071 -0.0404 0.7178 0.4256
-1.000 0.0610 0.00535 0.00065 -0.0407 0.6993 0.5602
-0.750 0.0890 0.00524 0.00065 -0.0408 0.6902 0.6075
-0.500 0.1173 0.00521 0.00064 -0.0409 0.6808 0.6261
-0.250 0.1456 0.00519 0.00064 -0.0410 0.6711 0.6431
0.000 0.1739 0.00520 0.00065 -0.0410 0.6614 0.6569
0.250 0.2022 0.00522 0.00066 -0.0411 0.6510 0.6680
0.500 0.2305 0.00524 0.00068 -0.0412 0.6394 0.6788
0.750 0.2586 0.00528 0.00071 -0.0413 0.6258 0.6888
1.000 0.2867 0.00533 0.00074 -0.0413 0.6096 0.6985
1.250 0.3143 0.00545 0.00078 -0.0413 0.5804 0.7085
1.500 0.3416 0.00562 0.00083 -0.0412 0.5397 0.7182
1.750 0.3685 0.00585 0.00091 -0.0411 0.4890 0.7277
2.000 0.3957 0.00606 0.00101 -0.0411 0.4482 0.7378
2.250 0.4207 0.00665 0.00120 -0.0409 0.3397 0.7476
2.500 0.4450 0.00739 0.00148 -0.0406 0.2167 0.7574
2.750 0.4706 0.00794 0.00173 -0.0405 0.1346 0.7677
3.000 0.4970 0.00829 0.00195 -0.0404 0.0899 0.7784
3.250 0.5234 0.00862 0.00216 -0.0403 0.0535 0.7890
3.500 0.5503 0.00886 0.00236 -0.0402 0.0363 0.7997
3.750 0.5775 0.00904 0.00255 -0.0401 0.0306 0.8110
4.000 0.6045 0.00922 0.00277 -0.0400 0.0252 0.8223
4.250 0.6314 0.00939 0.00298 -0.0399 0.0221 0.8336
4.500 0.6579 0.00963 0.00323 -0.0397 0.0170 0.8451
4.750 0.6844 0.00982 0.00347 -0.0395 0.0154 0.8572
5.000 0.7106 0.01006 0.00375 -0.0392 0.0139 0.8698
5.250 0.7363 0.01032 0.00406 -0.0389 0.0125 0.8833
5.500 0.7613 0.01064 0.00446 -0.0384 0.0117 0.8978
5.750 0.7855 0.01098 0.00490 -0.0377 0.0113 0.9142
6.000 0.8093 0.01125 0.00526 -0.0369 0.0111 0.9327
6.250 0.8329 0.01153 0.00564 -0.0361 0.0109 0.9584
6.500 0.8618 0.01186 0.00603 -0.0365 0.0106 1.0000
6.750 0.8879 0.01224 0.00644 -0.0364 0.0101 1.0000
7.000 0.9137 0.01265 0.00689 -0.0363 0.0097 1.0000
7.250 0.9392 0.01309 0.00737 -0.0361 0.0093 1.0000
7.500 0.9645 0.01353 0.00786 -0.0359 0.0089 1.0000
7.750 0.9896 0.01399 0.00834 -0.0356 0.0084 1.0000
8.000 1.0130 0.01472 0.00913 -0.0352 0.0078 1.0000
8.250 1.0361 0.01548 0.00997 -0.0347 0.0074 1.0000
8.500 1.0606 0.01596 0.01051 -0.0344 0.0073 1.0000
8.750 1.0848 0.01648 0.01110 -0.0340 0.0070 1.0000
9.000 1.1084 0.01705 0.01174 -0.0336 0.0068 1.0000
9.250 1.1318 0.01764 0.01243 -0.0332 0.0064 1.0000
9.500 1.1550 0.01824 0.01309 -0.0327 0.0061 1.0000
9.750 1.1783 0.01874 0.01365 -0.0324 0.0058 1.0000
10.000 1.2018 0.01920 0.01414 -0.0320 0.0055 1.0000
10.250 1.2249 0.01966 0.01463 -0.0316 0.0052 1.0000
10.500 1.2457 0.02045 0.01549 -0.0310 0.0049 1.0000
10.750 1.2659 0.02129 0.01642 -0.0302 0.0047 1.0000
11.000 1.2857 0.02212 0.01736 -0.0294 0.0046 1.0000
11.250 1.3047 0.02301 0.01836 -0.0286 0.0044 1.0000
11.500 1.3228 0.02394 0.01943 -0.0276 0.0042 1.0000
11.750 1.3401 0.02488 0.02047 -0.0266 0.0041 1.0000
12.000 1.3564 0.02585 0.02155 -0.0255 0.0039 1.0000
12.250 1.3715 0.02685 0.02265 -0.0243 0.0037 1.0000
12.500 1.3853 0.02786 0.02376 -0.0230 0.0036 1.0000
12.750 1.3951 0.02889 0.02488 -0.0210 0.0035 1.0000
13.000 1.4011 0.03004 0.02613 -0.0187 0.0034 1.0000
13.250 1.4065 0.03127 0.02746 -0.0166 0.0033 1.0000
13.500 1.4086 0.03288 0.02918 -0.0146 0.0032 1.0000
13.750 1.4081 0.03484 0.03129 -0.0129 0.0031 1.0000
14.000 1.4047 0.03724 0.03383 -0.0115 0.0030 1.0000
14.250 1.3985 0.04013 0.03688 -0.0106 0.0029 1.0000
14.500 1.3867 0.04388 0.04085 -0.0103 0.0029 1.0000
14.750 1.3715 0.04843 0.04559 -0.0109 0.0028 1.0000
15.000 1.3586 0.05314 0.05047 -0.0123 0.0028 1.0000
15.250 1.3402 0.05910 0.05661 -0.0148 0.0028 1.0000
15.500 1.3215 0.06578 0.06346 -0.0183 0.0028 1.0000
15.750 1.2962 0.07440 0.07227 -0.0235 0.0028 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63-209 (naca63209-il)