NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-210 (naca65210-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.6 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65210-il-1000000.txt Download as CSV file: xf-naca65210-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6529 0.05116 0.04922 -0.0470 1.0000 0.0090
-8.750 -0.6672 0.04593 0.04379 -0.0452 1.0000 0.0089
-8.500 -0.6822 0.04050 0.03812 -0.0422 1.0000 0.0086
-8.250 -0.6926 0.02584 0.02239 -0.0420 0.9901 0.0089
-8.000 -0.6728 0.01958 0.01534 -0.0430 0.9846 0.0096
-7.750 -0.6428 0.01853 0.01418 -0.0444 0.9795 0.0101
-7.500 -0.6122 0.01768 0.01321 -0.0456 0.9735 0.0105
-7.250 -0.5823 0.01693 0.01235 -0.0466 0.9665 0.0111
-7.000 -0.5556 0.01581 0.01107 -0.0468 0.9575 0.0117
-6.750 -0.5309 0.01496 0.01008 -0.0463 0.9475 0.0123
-6.500 -0.5060 0.01441 0.00941 -0.0459 0.9381 0.0129
-6.250 -0.4840 0.01309 0.00791 -0.0450 0.9283 0.0137
-6.000 -0.4607 0.01229 0.00705 -0.0444 0.9187 0.0145
-5.750 -0.4358 0.01191 0.00661 -0.0440 0.9102 0.0152
-5.500 -0.4109 0.01146 0.00609 -0.0435 0.9016 0.0159
-5.250 -0.3857 0.01100 0.00557 -0.0431 0.8933 0.0168
-5.000 -0.3603 0.01064 0.00513 -0.0428 0.8853 0.0177
-4.750 -0.3332 0.01055 0.00500 -0.0427 0.8771 0.0184
-4.500 -0.3104 0.00959 0.00390 -0.0420 0.8694 0.0197
-4.250 -0.2848 0.00913 0.00340 -0.0417 0.8615 0.0211
-4.000 -0.2583 0.00886 0.00308 -0.0416 0.8545 0.0226
-3.750 -0.2314 0.00863 0.00281 -0.0415 0.8468 0.0243
-3.500 -0.2042 0.00849 0.00262 -0.0414 0.8398 0.0257
-3.250 -0.1776 0.00812 0.00217 -0.0413 0.8323 0.0290
-3.000 -0.1504 0.00791 0.00193 -0.0413 0.8257 0.0334
-2.750 -0.1228 0.00776 0.00174 -0.0413 0.8185 0.0372
-2.500 -0.0962 0.00740 0.00151 -0.0413 0.8119 0.0807
-2.250 -0.0728 0.00615 0.00117 -0.0414 0.8045 0.3451
-2.000 -0.0485 0.00529 0.00099 -0.0413 0.7981 0.5547
-1.750 -0.0209 0.00512 0.00096 -0.0414 0.7913 0.6089
-1.500 0.0067 0.00505 0.00094 -0.0414 0.7849 0.6448
-1.250 0.0346 0.00498 0.00094 -0.0414 0.7783 0.6750
-1.000 0.0622 0.00495 0.00097 -0.0414 0.7720 0.7040
-0.750 0.0903 0.00494 0.00098 -0.0415 0.7657 0.7191
-0.500 0.1184 0.00495 0.00098 -0.0415 0.7592 0.7320
-0.250 0.1466 0.00497 0.00099 -0.0416 0.7533 0.7421
0.000 0.1750 0.00496 0.00099 -0.0418 0.7468 0.7483
0.250 0.2032 0.00499 0.00100 -0.0419 0.7409 0.7551
0.500 0.2317 0.00498 0.00102 -0.0421 0.7346 0.7615
0.750 0.2598 0.00501 0.00104 -0.0421 0.7279 0.7682
1.000 0.2881 0.00502 0.00106 -0.0423 0.7194 0.7749
1.250 0.3158 0.00504 0.00108 -0.0423 0.7058 0.7816
1.500 0.3435 0.00509 0.00109 -0.0422 0.6900 0.7886
1.750 0.3708 0.00513 0.00112 -0.0421 0.6727 0.7954
2.000 0.3981 0.00521 0.00116 -0.0421 0.6484 0.8026
2.250 0.4249 0.00531 0.00121 -0.0419 0.6198 0.8095
2.500 0.4516 0.00547 0.00128 -0.0417 0.5861 0.8171
2.750 0.4766 0.00577 0.00139 -0.0413 0.5221 0.8244
3.000 0.4956 0.00684 0.00175 -0.0401 0.3433 0.8324
3.250 0.5135 0.00810 0.00225 -0.0389 0.1494 0.8406
3.500 0.5349 0.00893 0.00264 -0.0381 0.0447 0.8487
3.750 0.5607 0.00922 0.00290 -0.0378 0.0336 0.8573
4.000 0.5863 0.00946 0.00320 -0.0374 0.0288 0.8654
4.250 0.6122 0.00970 0.00348 -0.0372 0.0257 0.8742
4.500 0.6356 0.01018 0.00405 -0.0364 0.0218 0.8831
4.750 0.6606 0.01044 0.00436 -0.0359 0.0206 0.8922
5.250 0.7091 0.01101 0.00505 -0.0346 0.0182 0.9126
5.500 0.7320 0.01135 0.00544 -0.0338 0.0172 0.9234
5.750 0.7533 0.01180 0.00595 -0.0326 0.0163 0.9354
6.000 0.7696 0.01269 0.00696 -0.0305 0.0154 0.9516
6.250 0.7902 0.01356 0.00794 -0.0293 0.0149 0.9731
6.500 0.8221 0.01382 0.00825 -0.0305 0.0143 1.0000
6.750 0.8468 0.01441 0.00888 -0.0302 0.0137 1.0000
7.000 0.8709 0.01509 0.00961 -0.0298 0.0131 1.0000
7.250 0.8948 0.01580 0.01038 -0.0294 0.0126 1.0000
7.500 0.9185 0.01653 0.01115 -0.0290 0.0122 1.0000
7.750 0.9423 0.01716 0.01183 -0.0287 0.0117 1.0000
8.000 0.9651 0.01799 0.01271 -0.0282 0.0113 1.0000
8.250 0.9831 0.02078 0.01573 -0.0271 0.0104 1.0000
8.500 1.0066 0.02126 0.01631 -0.0266 0.0101 1.0000
8.750 1.0284 0.02229 0.01748 -0.0260 0.0098 1.0000
9.000 1.0482 0.02389 0.01927 -0.0250 0.0093 1.0000
9.250 1.0672 0.02535 0.02091 -0.0240 0.0089 1.0000
9.500 1.0853 0.02666 0.02237 -0.0230 0.0086 1.0000
9.750 1.1014 0.02816 0.02404 -0.0218 0.0083 1.0000
10.000 1.1178 0.02920 0.02520 -0.0207 0.0081 1.0000
10.250 1.1327 0.03030 0.02641 -0.0194 0.0079 1.0000
10.500 1.1466 0.03124 0.02744 -0.0181 0.0077 1.0000
10.750 1.1228 0.03727 0.03400 -0.0131 0.0072 1.0000
11.000 1.1008 0.04114 0.03822 -0.0078 0.0071 1.0000
11.250 1.0880 0.04409 0.04140 -0.0045 0.0070 1.0000
11.500 1.0743 0.04732 0.04483 -0.0020 0.0070 1.0000
11.750 1.0382 0.05359 0.05140 -0.0001 0.0069 1.0000
12.000 0.9940 0.06167 0.05974 -0.0008 0.0070 1.0000
12.250 0.9643 0.06868 0.06691 -0.0036 0.0070 1.0000
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Polar data table (+)
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