NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD A (n64212ma-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.45 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212ma-il-1000000.txt Download as CSV file: xf-n64212ma-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD A
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4156 0.09816 0.09642 -0.0292 1.0000 0.0205
-10.250 -0.4207 0.09214 0.09041 -0.0327 1.0000 0.0206
-10.000 -0.4304 0.08564 0.08392 -0.0361 1.0000 0.0207
-9.750 -0.4263 0.08321 0.08152 -0.0366 1.0000 0.0209
-9.500 -0.4249 0.07975 0.07808 -0.0383 1.0000 0.0210
-9.250 -0.4237 0.07637 0.07472 -0.0402 1.0000 0.0211
-8.750 -0.4057 0.06341 0.06165 -0.0608 0.9510 0.0215
-8.500 -0.4147 0.05955 0.05757 -0.0630 0.9058 0.0217
-8.250 -0.4196 0.05676 0.05462 -0.0624 0.8807 0.0220
-8.000 -0.4196 0.05400 0.05173 -0.0619 0.8630 0.0227
-7.750 -0.4501 0.04285 0.03998 -0.0605 0.8496 0.0243
-7.500 -0.4372 0.04114 0.03816 -0.0598 0.8366 0.0244
-7.250 -0.4223 0.03945 0.03637 -0.0593 0.8250 0.0246
-7.000 -0.4058 0.03806 0.03486 -0.0587 0.8109 0.0248
-6.750 -0.3883 0.03645 0.03313 -0.0581 0.7960 0.0250
-6.500 -0.3700 0.03482 0.03136 -0.0575 0.7829 0.0255
-6.250 -0.3600 0.02853 0.02445 -0.0556 0.7729 0.0281
-6.000 -0.3381 0.02740 0.02323 -0.0552 0.7587 0.0283
-5.750 -0.3158 0.02638 0.02208 -0.0548 0.7406 0.0286
-5.500 -0.2928 0.02532 0.02088 -0.0544 0.7223 0.0289
-5.250 -0.2745 0.01949 0.01431 -0.0524 0.7114 0.0274
-5.000 -0.2508 0.01746 0.01196 -0.0517 0.6920 0.0274
-4.750 -0.2259 0.01586 0.01010 -0.0512 0.6736 0.0273
-4.500 -0.2000 0.01480 0.00881 -0.0507 0.6526 0.0274
-4.250 -0.1739 0.01404 0.00784 -0.0503 0.6249 0.0275
-4.000 -0.1477 0.01362 0.00719 -0.0498 0.5885 0.0277
-3.750 -0.1227 0.01279 0.00612 -0.0493 0.5392 0.0279
-3.500 -0.1051 0.01342 0.00571 -0.0479 0.2394 0.0283
-3.250 -0.0800 0.01333 0.00537 -0.0475 0.1644 0.0287
-3.000 -0.0540 0.01329 0.00515 -0.0472 0.1092 0.0292
-2.750 -0.0267 0.01308 0.00492 -0.0470 0.1054 0.0298
-2.500 0.0004 0.01278 0.00458 -0.0467 0.1039 0.0303
-2.250 0.0275 0.01252 0.00430 -0.0465 0.1025 0.0307
-2.000 0.0548 0.01233 0.00406 -0.0463 0.1013 0.0312
-1.750 0.0823 0.01218 0.00388 -0.0461 0.1003 0.0315
-1.500 0.1094 0.01194 0.00362 -0.0459 0.0995 0.0319
-1.250 0.1368 0.01169 0.00336 -0.0458 0.0990 0.0326
-1.000 0.1646 0.01158 0.00325 -0.0457 0.0985 0.0334
-0.750 0.1924 0.01150 0.00316 -0.0456 0.0980 0.0342
-0.500 0.2203 0.01147 0.00311 -0.0455 0.0975 0.0354
-0.250 0.2482 0.01140 0.00302 -0.0454 0.0971 0.0363
0.000 0.2761 0.01134 0.00296 -0.0454 0.0967 0.0377
0.250 0.3039 0.01134 0.00296 -0.0453 0.0962 0.0392
0.500 0.3318 0.01134 0.00295 -0.0452 0.0959 0.0411
0.750 0.3596 0.01136 0.00297 -0.0451 0.0956 0.0443
1.000 0.3873 0.01140 0.00301 -0.0450 0.0951 0.0500
1.250 0.4145 0.01144 0.00311 -0.0448 0.0942 0.0730
1.500 0.4406 0.00996 0.00312 -0.0457 0.0935 0.6200
1.750 0.4682 0.00991 0.00322 -0.0456 0.0929 0.6730
2.000 0.4957 0.00996 0.00334 -0.0454 0.0924 0.7048
2.250 0.5231 0.01004 0.00347 -0.0452 0.0920 0.7277
2.500 0.5504 0.01014 0.00360 -0.0450 0.0913 0.7483
2.750 0.5778 0.01025 0.00373 -0.0448 0.0906 0.7650
3.000 0.6046 0.01037 0.00389 -0.0444 0.0899 0.7869
3.250 0.6312 0.01053 0.00406 -0.0441 0.0892 0.8018
3.500 0.6574 0.01075 0.00428 -0.0438 0.0887 0.8116
3.750 0.6845 0.01087 0.00442 -0.0436 0.0882 0.8204
4.000 0.7121 0.01097 0.00452 -0.0435 0.0877 0.8285
4.250 0.7390 0.01106 0.00464 -0.0432 0.0871 0.8375
4.500 0.7662 0.01118 0.00477 -0.0430 0.0864 0.8465
4.750 0.7927 0.01128 0.00489 -0.0427 0.0856 0.8560
5.000 0.8194 0.01140 0.00501 -0.0424 0.0848 0.8661
5.250 0.8453 0.01152 0.00515 -0.0420 0.0840 0.8764
5.500 0.8717 0.01162 0.00527 -0.0417 0.0830 0.8871
5.750 0.8972 0.01169 0.00538 -0.0412 0.0820 0.8987
6.000 0.9227 0.01175 0.00547 -0.0406 0.0806 0.9113
6.250 0.9475 0.01180 0.00553 -0.0399 0.0790 0.9255
6.500 0.9706 0.01186 0.00565 -0.0389 0.0770 0.9428
7.000 1.0239 0.01227 0.00592 -0.0387 0.0524 1.0000
7.250 1.0487 0.01267 0.00631 -0.0384 0.0503 1.0000
7.500 1.0742 0.01298 0.00662 -0.0381 0.0484 1.0000
7.750 1.0986 0.01336 0.00700 -0.0377 0.0467 1.0000
8.000 1.1243 0.01358 0.00724 -0.0375 0.0445 1.0000
8.250 1.1495 0.01384 0.00750 -0.0371 0.0418 1.0000
8.500 1.1738 0.01416 0.00778 -0.0367 0.0373 1.0000
8.750 1.1972 0.01452 0.00811 -0.0362 0.0358 1.0000
9.000 1.2201 0.01491 0.00848 -0.0355 0.0348 1.0000
9.250 1.2427 0.01531 0.00888 -0.0348 0.0342 1.0000
9.500 1.2647 0.01572 0.00930 -0.0341 0.0337 1.0000
9.750 1.2857 0.01618 0.00978 -0.0332 0.0330 1.0000
10.000 1.3056 0.01670 0.01031 -0.0322 0.0324 1.0000
10.250 1.3247 0.01723 0.01086 -0.0310 0.0319 1.0000
10.500 1.3423 0.01776 0.01142 -0.0297 0.0316 1.0000
10.750 1.3587 0.01823 0.01192 -0.0280 0.0314 1.0000
11.000 1.3738 0.01874 0.01247 -0.0262 0.0312 1.0000
11.250 1.3882 0.01930 0.01307 -0.0244 0.0310 1.0000
11.500 1.4021 0.01991 0.01373 -0.0227 0.0308 1.0000
11.750 1.4156 0.02056 0.01443 -0.0210 0.0306 1.0000
12.000 1.4283 0.02129 0.01520 -0.0193 0.0304 1.0000
12.250 1.4401 0.02209 0.01605 -0.0176 0.0302 1.0000
12.500 1.4512 0.02297 0.01698 -0.0160 0.0300 1.0000
12.750 1.4618 0.02391 0.01798 -0.0145 0.0298 1.0000
13.000 1.4705 0.02502 0.01914 -0.0129 0.0296 1.0000
13.250 1.4769 0.02633 0.02050 -0.0113 0.0293 1.0000
13.500 1.4812 0.02785 0.02208 -0.0098 0.0291 1.0000
13.750 1.4826 0.02966 0.02397 -0.0082 0.0288 1.0000
14.000 1.4908 0.03103 0.02540 -0.0072 0.0288 1.0000
14.250 1.4987 0.03246 0.02690 -0.0064 0.0286 1.0000
14.500 1.5054 0.03405 0.02857 -0.0056 0.0285 1.0000
14.750 1.5113 0.03577 0.03036 -0.0049 0.0284 1.0000
15.000 1.5157 0.03769 0.03236 -0.0044 0.0282 1.0000
15.250 1.5190 0.03979 0.03453 -0.0040 0.0280 1.0000
15.500 1.5214 0.04205 0.03688 -0.0037 0.0278 1.0000
15.750 1.5225 0.04452 0.03944 -0.0036 0.0277 1.0000
16.000 1.5224 0.04724 0.04224 -0.0037 0.0275 1.0000
16.250 1.5214 0.05017 0.04526 -0.0041 0.0274 1.0000
16.500 1.5187 0.05346 0.04863 -0.0046 0.0272 1.0000
16.750 1.5153 0.05697 0.05222 -0.0055 0.0270 1.0000
17.000 1.5104 0.06082 0.05617 -0.0066 0.0269 1.0000
17.250 1.5042 0.06504 0.06048 -0.0081 0.0268 1.0000
17.500 1.4968 0.06960 0.06513 -0.0099 0.0267 1.0000
17.750 1.4873 0.07464 0.07026 -0.0120 0.0265 1.0000
18.000 1.4770 0.08000 0.07570 -0.0145 0.0264 1.0000
18.250 1.4663 0.08554 0.08133 -0.0171 0.0263 1.0000
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