NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 642-015 AIRFOIL (n64015-il) Reynolds number: 200,000 Max Cl/Cd: 44.98 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64015-il-200000-n5.txt Download as CSV file: xf-n64015-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 642-015 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8703 0.11308 0.10900 -0.0046 1.0000 0.0211
-16.000 -0.9150 0.09889 0.09453 -0.0137 1.0000 0.0209
-15.750 -0.9447 0.08935 0.08474 -0.0195 1.0000 0.0208
-15.500 -0.9678 0.08178 0.07695 -0.0237 1.0000 0.0209
-15.250 -0.9862 0.07551 0.07045 -0.0267 1.0000 0.0209
-15.000 -1.0015 0.07008 0.06479 -0.0290 1.0000 0.0209
-14.750 -1.0136 0.06540 0.05988 -0.0306 1.0000 0.0211
-14.500 -1.0235 0.06117 0.05542 -0.0318 1.0000 0.0212
-14.250 -1.0301 0.05752 0.05154 -0.0325 1.0000 0.0215
-14.000 -1.0348 0.05412 0.04791 -0.0329 1.0000 0.0217
-13.750 -1.0366 0.05119 0.04475 -0.0330 1.0000 0.0220
-13.500 -1.0371 0.04852 0.04184 -0.0329 1.0000 0.0224
-13.250 -1.0326 0.04614 0.03930 -0.0326 1.0000 0.0227
-13.000 -1.0245 0.04421 0.03731 -0.0323 1.0000 0.0230
-12.750 -1.0160 0.04244 0.03549 -0.0319 1.0000 0.0234
-12.500 -1.0065 0.04075 0.03371 -0.0315 1.0000 0.0238
-12.250 -0.9959 0.03913 0.03199 -0.0309 1.0000 0.0242
-12.000 -0.9845 0.03757 0.03033 -0.0304 1.0000 0.0246
-11.750 -0.9724 0.03611 0.02877 -0.0297 1.0000 0.0252
-11.500 -0.9590 0.03471 0.02726 -0.0291 1.0000 0.0257
-11.250 -0.9452 0.03338 0.02582 -0.0284 1.0000 0.0264
-11.000 -0.9308 0.03213 0.02446 -0.0276 1.0000 0.0270
-10.750 -0.9165 0.03091 0.02315 -0.0269 1.0000 0.0277
-10.500 -0.9038 0.02963 0.02187 -0.0260 1.0000 0.0283
-10.250 -0.8909 0.02851 0.02074 -0.0253 1.0000 0.0293
-10.000 -0.8771 0.02747 0.01968 -0.0245 1.0000 0.0304
-9.750 -0.8632 0.02645 0.01861 -0.0236 1.0000 0.0315
-9.500 -0.8491 0.02547 0.01757 -0.0226 1.0000 0.0325
-9.250 -0.8354 0.02450 0.01653 -0.0216 1.0000 0.0337
-9.000 -0.8250 0.02341 0.01546 -0.0203 1.0000 0.0348
-8.750 -0.8127 0.02253 0.01459 -0.0190 1.0000 0.0362
-8.500 -0.7893 0.02169 0.01368 -0.0197 0.9586 0.0383
-8.250 -0.7654 0.02097 0.01283 -0.0201 0.9340 0.0406
-8.000 -0.7522 0.02020 0.01204 -0.0185 0.9128 0.0430
-7.750 -0.7369 0.01963 0.01140 -0.0169 0.8960 0.0458
-7.250 -0.7058 0.01849 0.01013 -0.0135 0.8693 0.0534
-7.000 -0.6880 0.01799 0.00956 -0.0121 0.8574 0.0589
-6.750 -0.6704 0.01741 0.00897 -0.0107 0.8468 0.0671
-6.250 -0.6344 0.01621 0.00784 -0.0081 0.8270 0.1002
-6.000 -0.6166 0.01553 0.00729 -0.0069 0.8182 0.1327
-5.750 -0.5996 0.01470 0.00670 -0.0056 0.8090 0.1847
-5.500 -0.5841 0.01374 0.00607 -0.0042 0.8006 0.2588
-5.250 -0.5691 0.01273 0.00551 -0.0027 0.7920 0.3552
-5.000 -0.5496 0.01222 0.00534 -0.0015 0.7846 0.4426
-4.750 -0.5246 0.01206 0.00521 -0.0010 0.7768 0.4797
-4.500 -0.4993 0.01196 0.00509 -0.0004 0.7700 0.5072
-4.250 -0.4733 0.01190 0.00504 -0.0001 0.7620 0.5311
-4.000 -0.4473 0.01189 0.00499 0.0004 0.7554 0.5510
-3.750 -0.4205 0.01189 0.00497 0.0007 0.7478 0.5686
-3.500 -0.3940 0.01193 0.00498 0.0011 0.7412 0.5861
-3.250 -0.3667 0.01193 0.00494 0.0013 0.7349 0.5969
-3.000 -0.3388 0.01188 0.00480 0.0012 0.7281 0.6033
-2.750 -0.3110 0.01181 0.00464 0.0012 0.7224 0.6084
-2.500 -0.2828 0.01176 0.00457 0.0012 0.7158 0.6133
-2.250 -0.2548 0.01172 0.00445 0.0011 0.7093 0.6193
-2.000 -0.2267 0.01167 0.00432 0.0011 0.7037 0.6243
-1.750 -0.1983 0.01162 0.00426 0.0009 0.6971 0.6279
-1.500 -0.1702 0.01158 0.00417 0.0008 0.6916 0.6324
-1.250 -0.1419 0.01156 0.00408 0.0007 0.6865 0.6376
-0.750 -0.0851 0.01149 0.00400 0.0004 0.6755 0.6457
-0.500 -0.0568 0.01149 0.00395 0.0003 0.6710 0.6505
0.000 0.0000 0.01146 0.00394 0.0000 0.6599 0.6599
0.500 0.0568 0.01149 0.00395 -0.0003 0.6505 0.6710
0.750 0.0851 0.01149 0.00400 -0.0004 0.6457 0.6755
1.000 0.1134 0.01152 0.00404 -0.0005 0.6417 0.6806
1.250 0.1418 0.01156 0.00408 -0.0007 0.6376 0.6865
1.500 0.1701 0.01158 0.00417 -0.0008 0.6324 0.6916
1.750 0.1983 0.01162 0.00426 -0.0009 0.6279 0.6971
2.000 0.2267 0.01167 0.00432 -0.0011 0.6243 0.7038
2.250 0.2548 0.01172 0.00445 -0.0011 0.6193 0.7093
2.500 0.2828 0.01176 0.00457 -0.0012 0.6133 0.7157
2.750 0.3110 0.01181 0.00464 -0.0012 0.6084 0.7224
3.000 0.3388 0.01188 0.00480 -0.0012 0.6034 0.7281
3.250 0.3667 0.01193 0.00494 -0.0013 0.5969 0.7349
3.500 0.3940 0.01193 0.00498 -0.0011 0.5861 0.7412
3.750 0.4205 0.01189 0.00497 -0.0007 0.5686 0.7478
4.000 0.4473 0.01189 0.00499 -0.0004 0.5510 0.7554
4.250 0.4733 0.01190 0.00504 0.0001 0.5311 0.7620
4.500 0.4994 0.01196 0.00509 0.0004 0.5071 0.7700
4.750 0.5246 0.01206 0.00520 0.0010 0.4795 0.7768
5.000 0.5496 0.01222 0.00534 0.0015 0.4424 0.7846
5.250 0.5691 0.01273 0.00551 0.0027 0.3551 0.7920
5.500 0.5841 0.01374 0.00607 0.0042 0.2589 0.8006
5.750 0.5996 0.01471 0.00670 0.0056 0.1842 0.8090
6.000 0.6167 0.01553 0.00728 0.0069 0.1328 0.8182
6.250 0.6345 0.01621 0.00785 0.0081 0.1000 0.8270
6.750 0.6706 0.01741 0.00897 0.0107 0.0670 0.8467
7.000 0.6882 0.01799 0.00956 0.0120 0.0588 0.8574
7.250 0.7060 0.01850 0.01013 0.0134 0.0533 0.8694
7.500 0.7208 0.01912 0.01077 0.0152 0.0488 0.8820
7.750 0.7372 0.01963 0.01139 0.0168 0.0458 0.8960
8.000 0.7525 0.02021 0.01205 0.0184 0.0430 0.9127
8.250 0.7659 0.02097 0.01283 0.0200 0.0406 0.9339
8.500 0.7898 0.02168 0.01368 0.0196 0.0381 0.9584
8.750 0.8133 0.02253 0.01458 0.0189 0.0361 1.0000
9.000 0.8256 0.02341 0.01546 0.0201 0.0348 1.0000
9.250 0.8355 0.02455 0.01658 0.0215 0.0336 1.0000
9.500 0.8497 0.02548 0.01757 0.0225 0.0326 1.0000
9.750 0.8638 0.02646 0.01862 0.0235 0.0314 1.0000
10.000 0.8779 0.02748 0.01969 0.0243 0.0303 1.0000
10.250 0.8917 0.02850 0.02073 0.0251 0.0292 1.0000
10.500 0.9047 0.02962 0.02186 0.0259 0.0283 1.0000
10.750 0.9172 0.03094 0.02316 0.0267 0.0276 1.0000
11.000 0.9318 0.03213 0.02447 0.0275 0.0270 1.0000
11.250 0.9461 0.03338 0.02583 0.0282 0.0263 1.0000
11.500 0.9602 0.03472 0.02727 0.0289 0.0257 1.0000
11.750 0.9734 0.03611 0.02877 0.0296 0.0251 1.0000
12.000 0.9862 0.03758 0.03034 0.0302 0.0247 1.0000
12.250 0.9971 0.03913 0.03199 0.0308 0.0241 1.0000
12.500 1.0079 0.04076 0.03372 0.0313 0.0238 1.0000
12.750 1.0173 0.04244 0.03549 0.0317 0.0234 1.0000
13.000 1.0259 0.04422 0.03732 0.0321 0.0230 1.0000
13.250 1.0340 0.04618 0.03936 0.0324 0.0227 1.0000
13.500 1.0384 0.04847 0.04179 0.0327 0.0223 1.0000
13.750 1.0383 0.05116 0.04472 0.0328 0.0220 1.0000
14.000 1.0357 0.05421 0.04800 0.0327 0.0217 1.0000
14.250 1.0314 0.05753 0.05157 0.0323 0.0214 1.0000
14.500 1.0248 0.06122 0.05548 0.0315 0.0212 1.0000
14.750 1.0152 0.06541 0.05989 0.0304 0.0211 1.0000
15.000 1.0033 0.07006 0.06477 0.0288 0.0210 1.0000
15.250 0.9881 0.07549 0.07042 0.0265 0.0208 1.0000
15.500 0.9692 0.08184 0.07701 0.0234 0.0208 1.0000
15.750 0.9455 0.08954 0.08495 0.0191 0.0207 1.0000
16.000 0.9159 0.09910 0.09475 0.0133 0.0208 1.0000
16.250 0.8698 0.11371 0.10965 0.0039 0.0211 1.0000
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