NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 642-015A AIRFOIL (n64015a-il) Reynolds number: 200,000 Max Cl/Cd: 44.49 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64015a-il-200000-n5.txt Download as CSV file: xf-n64015a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 642-015A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.8974 0.10088 0.09652 -0.0205 1.0000 0.0203
-15.750 -0.9345 0.08982 0.08519 -0.0271 1.0000 0.0201
-15.500 -0.9604 0.08190 0.07703 -0.0313 1.0000 0.0201
-15.250 -0.9806 0.07547 0.07037 -0.0342 1.0000 0.0201
-15.000 -0.9968 0.07007 0.06475 -0.0362 1.0000 0.0202
-14.750 -1.0099 0.06537 0.05983 -0.0376 1.0000 0.0203
-14.500 -1.0200 0.06123 0.05548 -0.0384 1.0000 0.0204
-14.250 -1.0274 0.05754 0.05158 -0.0389 1.0000 0.0206
-14.000 -1.0324 0.05421 0.04803 -0.0390 1.0000 0.0208
-13.750 -1.0348 0.05122 0.04483 -0.0389 1.0000 0.0210
-13.500 -1.0349 0.04852 0.04193 -0.0385 1.0000 0.0213
-13.250 -1.0330 0.04607 0.03928 -0.0380 1.0000 0.0216
-13.000 -1.0292 0.04384 0.03683 -0.0373 1.0000 0.0220
-12.750 -1.0235 0.04182 0.03459 -0.0366 1.0000 0.0224
-12.500 -1.0149 0.03995 0.03260 -0.0358 1.0000 0.0228
-12.250 -1.0046 0.03832 0.03092 -0.0350 1.0000 0.0232
-12.000 -0.9938 0.03683 0.02935 -0.0342 1.0000 0.0236
-11.750 -0.9822 0.03540 0.02785 -0.0334 1.0000 0.0240
-11.500 -0.9700 0.03404 0.02641 -0.0325 1.0000 0.0244
-11.250 -0.9572 0.03273 0.02502 -0.0315 1.0000 0.0250
-11.000 -0.9440 0.03147 0.02367 -0.0305 1.0000 0.0255
-10.750 -0.9305 0.03027 0.02237 -0.0294 1.0000 0.0262
-10.500 -0.9168 0.02912 0.02111 -0.0283 1.0000 0.0268
-10.250 -0.9030 0.02804 0.01993 -0.0271 1.0000 0.0275
-10.000 -0.8920 0.02684 0.01872 -0.0257 1.0000 0.0282
-9.750 -0.8799 0.02585 0.01772 -0.0243 1.0000 0.0292
-9.500 -0.8671 0.02498 0.01682 -0.0228 1.0000 0.0303
-9.250 -0.8546 0.02415 0.01593 -0.0211 1.0000 0.0316
-9.000 -0.8428 0.02337 0.01509 -0.0191 1.0000 0.0329
-8.750 -0.8343 0.02256 0.01426 -0.0165 1.0000 0.0341
-8.500 -0.8264 0.02184 0.01355 -0.0137 1.0000 0.0355
-8.250 -0.8167 0.02123 0.01292 -0.0110 1.0000 0.0371
-8.000 -0.8086 0.02070 0.01234 -0.0080 1.0000 0.0390
-7.750 -0.7870 0.01997 0.01160 -0.0078 0.9941 0.0420
-7.500 -0.7568 0.01924 0.01085 -0.0092 0.9834 0.0468
-7.250 -0.7275 0.01850 0.01010 -0.0105 0.9719 0.0524
-7.000 -0.6983 0.01784 0.00942 -0.0115 0.9602 0.0601
-6.750 -0.6707 0.01719 0.00879 -0.0122 0.9471 0.0707
-6.500 -0.6450 0.01653 0.00818 -0.0124 0.9335 0.0859
-6.250 -0.6206 0.01587 0.00760 -0.0124 0.9199 0.1091
-6.000 -0.5992 0.01511 0.00702 -0.0118 0.9061 0.1477
-5.750 -0.5803 0.01426 0.00643 -0.0108 0.8927 0.2044
-5.500 -0.5642 0.01332 0.00583 -0.0092 0.8797 0.2829
-5.250 -0.5506 0.01239 0.00537 -0.0071 0.8666 0.3804
-5.000 -0.5316 0.01195 0.00520 -0.0055 0.8551 0.4583
-4.750 -0.5082 0.01177 0.00507 -0.0046 0.8452 0.4981
-4.500 -0.4837 0.01166 0.00494 -0.0038 0.8349 0.5254
-4.250 -0.4585 0.01157 0.00483 -0.0033 0.8256 0.5450
-4.000 -0.4329 0.01151 0.00472 -0.0027 0.8166 0.5624
-3.750 -0.4077 0.01149 0.00467 -0.0021 0.8077 0.5832
-3.500 -0.3825 0.01149 0.00463 -0.0014 0.7994 0.6033
-3.250 -0.3565 0.01148 0.00460 -0.0010 0.7907 0.6172
-3.000 -0.3297 0.01146 0.00454 -0.0006 0.7831 0.6273
-2.750 -0.3029 0.01143 0.00444 -0.0004 0.7753 0.6364
-2.500 -0.2755 0.01139 0.00436 -0.0003 0.7678 0.6426
-2.250 -0.2483 0.01135 0.00423 -0.0002 0.7604 0.6491
-2.000 -0.2208 0.01130 0.00415 -0.0002 0.7527 0.6542
-1.750 -0.1932 0.01127 0.00407 -0.0001 0.7461 0.6595
-1.500 -0.1658 0.01124 0.00399 -0.0001 0.7389 0.6658
-1.250 -0.1380 0.01121 0.00393 -0.0001 0.7328 0.6709
-1.000 -0.1105 0.01118 0.00390 -0.0001 0.7255 0.6764
-0.750 -0.0830 0.01117 0.00382 0.0000 0.7188 0.6827
-0.500 -0.0552 0.01115 0.00381 0.0000 0.7126 0.6879
-0.250 -0.0277 0.01115 0.00381 0.0000 0.7060 0.6942
0.000 0.0000 0.01115 0.00378 0.0000 0.7005 0.7005
0.250 0.0277 0.01115 0.00381 0.0000 0.6942 0.7060
0.500 0.0552 0.01115 0.00381 0.0000 0.6879 0.7126
0.750 0.0830 0.01117 0.00382 0.0000 0.6827 0.7188
1.000 0.1105 0.01118 0.00390 0.0001 0.6764 0.7256
1.250 0.1380 0.01121 0.00393 0.0001 0.6709 0.7328
1.500 0.1658 0.01124 0.00399 0.0001 0.6658 0.7389
1.750 0.1932 0.01127 0.00407 0.0001 0.6595 0.7462
2.000 0.2208 0.01130 0.00415 0.0002 0.6542 0.7527
2.250 0.2483 0.01135 0.00423 0.0002 0.6491 0.7604
2.500 0.2756 0.01139 0.00436 0.0003 0.6426 0.7678
2.750 0.3029 0.01143 0.00444 0.0004 0.6364 0.7753
3.000 0.3298 0.01146 0.00454 0.0006 0.6273 0.7831
3.250 0.3565 0.01148 0.00460 0.0010 0.6172 0.7908
3.500 0.3825 0.01149 0.00463 0.0014 0.6033 0.7994
3.750 0.4078 0.01149 0.00467 0.0021 0.5832 0.8077
4.000 0.4329 0.01151 0.00472 0.0027 0.5624 0.8166
4.250 0.4585 0.01157 0.00483 0.0033 0.5450 0.8256
4.500 0.4838 0.01166 0.00494 0.0038 0.5253 0.8349
4.750 0.5083 0.01177 0.00507 0.0045 0.4981 0.8452
5.000 0.5316 0.01195 0.00520 0.0055 0.4582 0.8551
5.250 0.5506 0.01239 0.00537 0.0070 0.3801 0.8666
5.500 0.5643 0.01332 0.00583 0.0092 0.2828 0.8797
5.750 0.5804 0.01426 0.00643 0.0107 0.2042 0.8926
6.000 0.5993 0.01511 0.00702 0.0118 0.1477 0.9061
6.250 0.6207 0.01587 0.00760 0.0124 0.1090 0.9199
6.500 0.6451 0.01653 0.00818 0.0124 0.0859 0.9335
6.750 0.6708 0.01719 0.00879 0.0121 0.0706 0.9471
7.000 0.6984 0.01784 0.00942 0.0115 0.0601 0.9602
7.250 0.7276 0.01850 0.01010 0.0104 0.0524 0.9720
7.500 0.7569 0.01924 0.01085 0.0092 0.0468 0.9835
7.750 0.7871 0.01997 0.01160 0.0077 0.0420 0.9941
8.000 0.8086 0.02069 0.01234 0.0080 0.0390 1.0000
8.250 0.8168 0.02123 0.01291 0.0110 0.0371 1.0000
8.500 0.8266 0.02184 0.01354 0.0136 0.0355 1.0000
8.750 0.8346 0.02256 0.01426 0.0165 0.0341 1.0000
9.000 0.8432 0.02337 0.01509 0.0190 0.0329 1.0000
9.250 0.8550 0.02415 0.01593 0.0210 0.0316 1.0000
9.500 0.8676 0.02498 0.01682 0.0227 0.0303 1.0000
9.750 0.8804 0.02585 0.01772 0.0242 0.0292 1.0000
10.000 0.8927 0.02684 0.01872 0.0256 0.0282 1.0000
10.250 0.9037 0.02804 0.01993 0.0270 0.0275 1.0000
10.500 0.9176 0.02912 0.02111 0.0282 0.0268 1.0000
10.750 0.9313 0.03027 0.02237 0.0293 0.0262 1.0000
11.000 0.9448 0.03147 0.02367 0.0304 0.0255 1.0000
11.250 0.9581 0.03273 0.02502 0.0314 0.0249 1.0000
11.500 0.9709 0.03404 0.02641 0.0323 0.0244 1.0000
11.750 0.9832 0.03540 0.02785 0.0332 0.0240 1.0000
12.000 0.9948 0.03683 0.02935 0.0340 0.0236 1.0000
12.250 1.0057 0.03832 0.03092 0.0348 0.0232 1.0000
12.500 1.0160 0.03995 0.03260 0.0356 0.0228 1.0000
12.750 1.0247 0.04182 0.03459 0.0364 0.0224 1.0000
13.000 1.0304 0.04385 0.03684 0.0371 0.0220 1.0000
13.250 1.0342 0.04608 0.03929 0.0378 0.0216 1.0000
13.500 1.0361 0.04852 0.04194 0.0383 0.0213 1.0000
13.750 1.0361 0.05123 0.04485 0.0387 0.0210 1.0000
14.000 1.0337 0.05423 0.04805 0.0388 0.0208 1.0000
14.250 1.0288 0.05755 0.05160 0.0387 0.0206 1.0000
14.500 1.0214 0.06125 0.05551 0.0382 0.0204 1.0000
14.750 1.0113 0.06540 0.05986 0.0373 0.0203 1.0000
15.000 0.9984 0.07009 0.06477 0.0359 0.0202 1.0000
15.250 0.9821 0.07551 0.07041 0.0339 0.0201 1.0000
15.500 0.9619 0.08194 0.07707 0.0309 0.0201 1.0000
15.750 0.9358 0.08994 0.08532 0.0267 0.0201 1.0000
16.000 0.8982 0.10112 0.09677 0.0200 0.0203 1.0000
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