NACA 63-210 AIRFOIL (n63210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-210 AIRFOIL (n63210-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.02 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63210-il-1000000.txt Download as CSV file: xf-n63210-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-210 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8792 0.07479 0.07311 -0.0246 1.0000 0.0059
-13.500 -0.9188 0.05971 0.05783 -0.0358 1.0000 0.0058
-13.250 -0.9614 0.04873 0.04662 -0.0441 1.0000 0.0058
-13.000 -0.9818 0.04295 0.04065 -0.0475 1.0000 0.0058
-12.750 -0.9952 0.03889 0.03641 -0.0490 1.0000 0.0058
-12.500 -1.0224 0.03423 0.03149 -0.0487 1.0000 0.0058
-12.250 -1.0391 0.03137 0.02839 -0.0461 1.0000 0.0058
-12.000 -1.0394 0.02905 0.02584 -0.0445 1.0000 0.0058
-11.750 -1.0467 0.02518 0.02152 -0.0424 1.0000 0.0060
-11.500 -1.0385 0.02288 0.01894 -0.0411 1.0000 0.0063
-11.250 -1.0221 0.02156 0.01747 -0.0404 1.0000 0.0065
-11.000 -1.0027 0.02058 0.01639 -0.0397 1.0000 0.0067
-10.750 -0.9817 0.01981 0.01554 -0.0393 1.0000 0.0069
-10.500 -0.9595 0.01920 0.01486 -0.0388 1.0000 0.0072
-10.250 -0.9374 0.01852 0.01409 -0.0384 1.0000 0.0075
-10.000 -0.9155 0.01775 0.01323 -0.0379 1.0000 0.0078
-9.750 -0.8935 0.01701 0.01236 -0.0373 1.0000 0.0082
-9.500 -0.8714 0.01627 0.01156 -0.0368 1.0000 0.0087
-9.250 -0.8451 0.01643 0.01176 -0.0366 1.0000 0.0092
-9.000 -0.8195 0.01654 0.01190 -0.0363 1.0000 0.0098
-8.750 -0.7948 0.01655 0.01190 -0.0359 1.0000 0.0108
-8.500 -0.7699 0.01674 0.01205 -0.0354 1.0000 0.0115
-8.250 -0.7497 0.01610 0.01137 -0.0345 1.0000 0.0125
-8.000 -0.7273 0.01616 0.01146 -0.0337 1.0000 0.0131
-7.750 -0.7004 0.01612 0.01141 -0.0339 0.9991 0.0141
-7.500 -0.6649 0.01606 0.01131 -0.0358 0.9964 0.0153
-7.250 -0.6280 0.01637 0.01156 -0.0379 0.9939 0.0160
-7.000 -0.5989 0.01417 0.00922 -0.0392 0.9897 0.0175
-6.750 -0.5648 0.01368 0.00873 -0.0409 0.9856 0.0185
-6.500 -0.5315 0.01318 0.00819 -0.0424 0.9806 0.0194
-6.250 -0.5003 0.01278 0.00775 -0.0434 0.9729 0.0204
-6.000 -0.4715 0.01248 0.00739 -0.0437 0.9628 0.0212
-5.750 -0.4443 0.01259 0.00745 -0.0435 0.9504 0.0221
-5.500 -0.4227 0.01133 0.00609 -0.0425 0.9333 0.0228
-5.250 -0.3993 0.01074 0.00541 -0.0416 0.9118 0.0229
-5.000 -0.3754 0.01028 0.00483 -0.0408 0.8900 0.0229
-4.750 -0.3502 0.00988 0.00432 -0.0403 0.8750 0.0229
-4.500 -0.3241 0.00953 0.00387 -0.0401 0.8635 0.0230
-4.250 -0.2975 0.00918 0.00343 -0.0399 0.8541 0.0232
-4.000 -0.2704 0.00888 0.00305 -0.0398 0.8452 0.0234
-3.750 -0.2428 0.00863 0.00273 -0.0398 0.8370 0.0235
-3.500 -0.2152 0.00840 0.00243 -0.0398 0.8287 0.0238
-3.250 -0.1872 0.00818 0.00217 -0.0398 0.8202 0.0243
-3.000 -0.1593 0.00801 0.00194 -0.0399 0.8120 0.0254
-2.750 -0.1311 0.00784 0.00175 -0.0399 0.8030 0.0270
-2.500 -0.1030 0.00771 0.00159 -0.0400 0.7945 0.0291
-2.250 -0.0749 0.00751 0.00143 -0.0401 0.7857 0.0496
-2.000 -0.0476 0.00682 0.00119 -0.0405 0.7768 0.1857
-1.750 -0.0207 0.00595 0.00096 -0.0410 0.7683 0.3812
-1.500 0.0070 0.00552 0.00088 -0.0413 0.7593 0.4909
-1.250 0.0352 0.00534 0.00090 -0.0414 0.7507 0.5613
-1.000 0.0636 0.00534 0.00091 -0.0415 0.7419 0.5956
-0.750 0.0920 0.00526 0.00088 -0.0416 0.7333 0.6147
-0.500 0.1203 0.00521 0.00086 -0.0417 0.7250 0.6321
-0.250 0.1488 0.00517 0.00086 -0.0418 0.7159 0.6469
0.000 0.1772 0.00516 0.00087 -0.0419 0.7062 0.6605
0.250 0.2054 0.00517 0.00089 -0.0419 0.6914 0.6798
0.500 0.2336 0.00519 0.00090 -0.0419 0.6758 0.6971
0.750 0.2620 0.00522 0.00092 -0.0420 0.6626 0.7080
1.000 0.2903 0.00525 0.00095 -0.0421 0.6474 0.7188
1.250 0.3184 0.00530 0.00098 -0.0421 0.6286 0.7299
1.500 0.3461 0.00541 0.00101 -0.0421 0.5977 0.7413
1.750 0.3734 0.00557 0.00106 -0.0420 0.5575 0.7529
2.000 0.4003 0.00580 0.00114 -0.0419 0.5060 0.7645
2.250 0.4261 0.00622 0.00127 -0.0417 0.4245 0.7760
2.500 0.4485 0.00729 0.00163 -0.0413 0.2462 0.7877
2.750 0.4715 0.00831 0.00205 -0.0409 0.0928 0.7996
3.000 0.4969 0.00884 0.00235 -0.0406 0.0300 0.8113
3.250 0.5241 0.00902 0.00254 -0.0405 0.0247 0.8225
3.500 0.5513 0.00917 0.00275 -0.0404 0.0237 0.8336
3.750 0.5783 0.00935 0.00298 -0.0402 0.0230 0.8450
4.000 0.6051 0.00956 0.00324 -0.0400 0.0223 0.8566
4.250 0.6313 0.00978 0.00354 -0.0397 0.0216 0.8685
4.500 0.6569 0.01004 0.00387 -0.0393 0.0209 0.8814
4.750 0.6820 0.01034 0.00424 -0.0387 0.0204 0.8949
5.000 0.7063 0.01067 0.00466 -0.0380 0.0200 0.9096
5.250 0.7295 0.01103 0.00509 -0.0370 0.0198 0.9261
5.500 0.7514 0.01141 0.00556 -0.0358 0.0197 0.9441
5.750 0.7730 0.01179 0.00603 -0.0345 0.0197 0.9689
6.000 0.8013 0.01234 0.00664 -0.0350 0.0194 1.0000
6.250 0.8265 0.01294 0.00728 -0.0347 0.0193 1.0000
6.500 0.8512 0.01361 0.00800 -0.0344 0.0193 1.0000
6.750 0.8755 0.01433 0.00876 -0.0340 0.0193 1.0000
7.000 0.8995 0.01511 0.00960 -0.0335 0.0191 1.0000
7.250 0.9219 0.01624 0.01076 -0.0330 0.0184 1.0000
7.500 0.9425 0.01848 0.01311 -0.0321 0.0178 1.0000
7.750 0.9686 0.01837 0.01306 -0.0321 0.0171 1.0000
8.000 0.9938 0.01872 0.01347 -0.0318 0.0166 1.0000
8.250 1.0180 0.01934 0.01416 -0.0315 0.0160 1.0000
8.500 1.0417 0.02002 0.01491 -0.0311 0.0154 1.0000
8.750 1.0651 0.02062 0.01556 -0.0308 0.0147 1.0000
9.000 1.0881 0.02116 0.01614 -0.0304 0.0141 1.0000
9.250 1.1102 0.02182 0.01681 -0.0300 0.0136 1.0000
9.500 1.1244 0.02495 0.02015 -0.0289 0.0125 1.0000
9.750 1.1485 0.02457 0.01983 -0.0285 0.0122 1.0000
10.000 1.1712 0.02472 0.02005 -0.0280 0.0116 1.0000
10.250 1.1927 0.02509 0.02048 -0.0274 0.0109 1.0000
10.500 1.2147 0.02515 0.02057 -0.0269 0.0103 1.0000
10.750 1.2366 0.02518 0.02060 -0.0265 0.0099 1.0000
11.000 1.2582 0.02520 0.02059 -0.0260 0.0095 1.0000
11.250 1.2717 0.02641 0.02187 -0.0247 0.0089 1.0000
11.500 1.2936 0.02641 0.02193 -0.0241 0.0086 1.0000
11.750 1.3130 0.02673 0.02233 -0.0232 0.0081 1.0000
12.000 1.3306 0.02695 0.02259 -0.0220 0.0075 1.0000
12.250 1.3449 0.02738 0.02305 -0.0204 0.0072 1.0000
12.500 1.3644 0.02734 0.02299 -0.0195 0.0069 1.0000
12.750 1.3814 0.02760 0.02324 -0.0184 0.0067 1.0000
13.000 1.3929 0.02837 0.02403 -0.0169 0.0062 1.0000
13.250 1.3963 0.02993 0.02574 -0.0149 0.0061 1.0000
13.500 1.4011 0.03145 0.02739 -0.0133 0.0059 1.0000
13.750 1.4017 0.03346 0.02954 -0.0118 0.0058 1.0000
14.000 1.4055 0.03526 0.03146 -0.0108 0.0056 1.0000
14.250 1.4081 0.03727 0.03359 -0.0100 0.0055 1.0000
14.500 1.4093 0.03955 0.03598 -0.0094 0.0053 1.0000
14.750 1.4065 0.04239 0.03897 -0.0092 0.0053 1.0000
15.000 1.4052 0.04522 0.04192 -0.0093 0.0052 1.0000
15.250 1.4013 0.04854 0.04536 -0.0098 0.0051 1.0000
15.500 1.3996 0.05175 0.04868 -0.0105 0.0050 1.0000
15.750 1.3867 0.05669 0.05379 -0.0122 0.0050 1.0000
16.000 1.3770 0.06151 0.05874 -0.0142 0.0049 1.0000
16.250 1.3536 0.06888 0.06632 -0.0178 0.0049 1.0000
16.500 1.3290 0.07724 0.07489 -0.0224 0.0049 1.0000
16.750 1.3043 0.08640 0.08422 -0.0280 0.0049 1.0000
17.000 1.2233 0.10969 0.10792 -0.0428 0.0052 1.0000
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Polar data table (+)
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