NACA 747A415 (naca747a415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 747A415 (naca747a415-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.64 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca747a415-il-1000000.txt Download as CSV file: xf-naca747a415-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 747A415
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.8034 0.06580 0.06367 -0.0573 1.0000 0.0137
-14.750 -0.8531 0.05333 0.05093 -0.0668 1.0000 0.0136
-14.500 -0.8750 0.04772 0.04513 -0.0695 1.0000 0.0137
-14.250 -0.9012 0.04265 0.03985 -0.0703 1.0000 0.0137
-14.000 -0.8991 0.04085 0.03794 -0.0700 1.0000 0.0138
-13.750 -0.9111 0.03790 0.03482 -0.0688 1.0000 0.0138
-13.500 -0.9286 0.03463 0.03133 -0.0667 1.0000 0.0139
-13.250 -0.9378 0.03014 0.02639 -0.0672 0.9320 0.0142
-13.000 -0.9370 0.02897 0.02506 -0.0644 0.9047 0.0144
-12.750 -0.9342 0.02793 0.02387 -0.0616 0.8854 0.0145
-12.500 -0.9296 0.02697 0.02276 -0.0589 0.8689 0.0146
-12.250 -0.9215 0.02632 0.02201 -0.0563 0.8539 0.0148
-12.000 -0.9121 0.02581 0.02140 -0.0538 0.8399 0.0150
-11.750 -0.9039 0.02492 0.02035 -0.0512 0.8269 0.0152
-11.500 -0.8893 0.02433 0.01964 -0.0494 0.8143 0.0155
-11.250 -0.8739 0.02363 0.01881 -0.0479 0.8018 0.0157
-11.000 -0.8581 0.02273 0.01775 -0.0464 0.7906 0.0160
-10.750 -0.8407 0.02198 0.01684 -0.0450 0.7803 0.0164
-10.500 -0.8219 0.02128 0.01599 -0.0439 0.7702 0.0166
-10.250 -0.8022 0.02058 0.01515 -0.0428 0.7614 0.0168
-10.000 -0.7832 0.01960 0.01399 -0.0417 0.7527 0.0171
-9.750 -0.7648 0.01830 0.01257 -0.0406 0.7452 0.0176
-9.500 -0.7429 0.01776 0.01197 -0.0399 0.7374 0.0179
-9.250 -0.7203 0.01727 0.01141 -0.0392 0.7305 0.0183
-9.000 -0.6970 0.01682 0.01089 -0.0386 0.7235 0.0186
-8.750 -0.6739 0.01633 0.01030 -0.0380 0.7167 0.0190
-8.500 -0.6498 0.01589 0.00980 -0.0375 0.7106 0.0195
-8.250 -0.6253 0.01552 0.00936 -0.0371 0.7042 0.0200
-8.000 -0.6005 0.01522 0.00896 -0.0366 0.6981 0.0204
-7.750 -0.5779 0.01443 0.00809 -0.0359 0.6921 0.0208
-7.500 -0.5553 0.01378 0.00739 -0.0352 0.6858 0.0215
-7.250 -0.5306 0.01341 0.00700 -0.0348 0.6799 0.0220
-7.000 -0.5055 0.01308 0.00663 -0.0344 0.6737 0.0225
-6.750 -0.4804 0.01278 0.00627 -0.0340 0.6677 0.0232
-6.500 -0.4546 0.01252 0.00596 -0.0338 0.6623 0.0239
-6.250 -0.4284 0.01229 0.00569 -0.0335 0.6564 0.0244
-6.000 -0.4055 0.01173 0.00507 -0.0328 0.6507 0.0255
-5.750 -0.3800 0.01142 0.00475 -0.0325 0.6456 0.0263
-5.500 -0.3538 0.01119 0.00449 -0.0322 0.6399 0.0274
-5.250 -0.3277 0.01099 0.00424 -0.0320 0.6344 0.0284
-5.000 -0.3009 0.01081 0.00403 -0.0319 0.6295 0.0292
-4.750 -0.2758 0.01045 0.00365 -0.0315 0.6243 0.0313
-4.500 -0.2492 0.01029 0.00346 -0.0313 0.6191 0.0331
-4.250 -0.2221 0.01014 0.00328 -0.0312 0.6145 0.0347
-4.000 -0.1960 0.00987 0.00302 -0.0310 0.6097 0.0381
-3.750 -0.1688 0.00975 0.00287 -0.0309 0.6049 0.0410
-3.500 -0.1424 0.00956 0.00268 -0.0308 0.6003 0.0469
-3.250 -0.1153 0.00937 0.00253 -0.0307 0.5963 0.0544
-3.000 -0.0884 0.00920 0.00239 -0.0306 0.5920 0.0649
-2.750 -0.0618 0.00903 0.00225 -0.0305 0.5877 0.0828
-2.500 -0.0365 0.00871 0.00212 -0.0303 0.5835 0.1323
-2.250 -0.0124 0.00822 0.00197 -0.0299 0.5800 0.2252
-2.000 0.0096 0.00756 0.00180 -0.0292 0.5764 0.3646
-1.750 0.0301 0.00679 0.00161 -0.0283 0.5729 0.5348
-1.500 0.0489 0.00607 0.00156 -0.0267 0.5693 0.7309
-1.250 0.0767 0.00608 0.00161 -0.0267 0.5666 0.7678
-1.000 0.1053 0.00611 0.00166 -0.0268 0.5637 0.7851
-0.750 0.1337 0.00616 0.00171 -0.0269 0.5608 0.7961
-0.500 0.1623 0.00623 0.00175 -0.0270 0.5580 0.8052
-0.250 0.1904 0.00636 0.00185 -0.0269 0.5552 0.8170
0.000 0.2176 0.00652 0.00202 -0.0266 0.5523 0.8295
0.250 0.2451 0.00664 0.00218 -0.0263 0.5504 0.8402
0.500 0.2734 0.00674 0.00230 -0.0263 0.5483 0.8464
0.750 0.3023 0.00682 0.00235 -0.0266 0.5461 0.8501
1.000 0.3312 0.00684 0.00235 -0.0269 0.5438 0.8524
1.250 0.3597 0.00687 0.00237 -0.0271 0.5415 0.8546
1.500 0.3882 0.00694 0.00242 -0.0273 0.5393 0.8567
1.750 0.4167 0.00704 0.00249 -0.0275 0.5369 0.8588
2.000 0.4457 0.00707 0.00253 -0.0279 0.5355 0.8605
2.250 0.4748 0.00710 0.00257 -0.0283 0.5340 0.8620
2.500 0.5039 0.00713 0.00261 -0.0287 0.5322 0.8635
2.750 0.5330 0.00716 0.00264 -0.0291 0.5298 0.8649
3.000 0.5620 0.00720 0.00267 -0.0295 0.5271 0.8661
3.250 0.5908 0.00727 0.00272 -0.0299 0.5243 0.8672
3.500 0.6193 0.00735 0.00279 -0.0302 0.5215 0.8686
3.750 0.6479 0.00738 0.00284 -0.0306 0.5196 0.8701
4.000 0.6766 0.00738 0.00289 -0.0309 0.5168 0.8714
4.250 0.7051 0.00739 0.00292 -0.0312 0.5126 0.8727
4.500 0.7332 0.00745 0.00298 -0.0314 0.5084 0.8741
4.750 0.7612 0.00752 0.00305 -0.0316 0.5032 0.8756
5.000 0.7896 0.00751 0.00308 -0.0319 0.4967 0.8771
5.250 0.8170 0.00761 0.00315 -0.0321 0.4899 0.8787
5.500 0.8454 0.00762 0.00321 -0.0324 0.4835 0.8803
5.750 0.8733 0.00769 0.00330 -0.0326 0.4777 0.8820
6.000 0.9009 0.00778 0.00339 -0.0328 0.4709 0.8835
6.250 0.9281 0.00784 0.00346 -0.0329 0.4599 0.8851
6.500 0.9546 0.00793 0.00356 -0.0329 0.4448 0.8870
6.750 0.9796 0.00812 0.00369 -0.0327 0.4178 0.8888
7.000 0.9946 0.00889 0.00413 -0.0310 0.3480 0.8913
7.250 1.0066 0.00983 0.00476 -0.0288 0.2854 0.8944
7.500 1.0169 0.01077 0.00541 -0.0264 0.2281 0.8976
7.750 1.0265 0.01162 0.00602 -0.0239 0.1824 0.9008
8.000 1.0317 0.01243 0.00665 -0.0205 0.1423 0.9051
8.250 1.0318 0.01314 0.00723 -0.0161 0.1139 0.9107
8.500 1.0310 0.01398 0.00797 -0.0119 0.0905 0.9165
8.750 1.0318 0.01482 0.00876 -0.0082 0.0713 0.9233
9.000 1.0334 0.01580 0.00967 -0.0050 0.0545 0.9307
9.250 1.0342 0.01684 0.01068 -0.0018 0.0406 0.9406
9.500 1.0411 0.01777 0.01162 0.0002 0.0341 0.9523
9.750 1.0589 0.01875 0.01265 0.0000 0.0299 0.9673
10.000 1.0870 0.01987 0.01381 -0.0026 0.0262 0.9834
10.250 1.0977 0.02104 0.01498 -0.0018 0.0242 1.0000
10.500 1.1084 0.02219 0.01616 -0.0009 0.0226 1.0000
10.750 1.1202 0.02328 0.01728 -0.0001 0.0214 1.0000
11.000 1.1286 0.02462 0.01863 0.0008 0.0199 1.0000
11.250 1.1356 0.02610 0.02015 0.0019 0.0189 1.0000
11.500 1.1468 0.02728 0.02137 0.0025 0.0184 1.0000
11.750 1.1574 0.02852 0.02265 0.0032 0.0175 1.0000
12.000 1.1660 0.02993 0.02408 0.0040 0.0168 1.0000
12.250 1.1714 0.03163 0.02581 0.0048 0.0162 1.0000
12.500 1.1764 0.03339 0.02763 0.0056 0.0154 1.0000
12.750 1.1845 0.03494 0.02923 0.0062 0.0152 1.0000
13.000 1.1936 0.03645 0.03079 0.0067 0.0148 1.0000
13.250 1.2014 0.03810 0.03248 0.0071 0.0143 1.0000
13.500 1.2089 0.03980 0.03423 0.0075 0.0140 1.0000
13.750 1.2159 0.04160 0.03607 0.0079 0.0137 1.0000
14.000 1.2219 0.04351 0.03804 0.0082 0.0136 1.0000
14.250 1.2242 0.04582 0.04038 0.0085 0.0131 1.0000
14.500 1.2232 0.04852 0.04315 0.0088 0.0128 1.0000
14.750 1.2252 0.05097 0.04566 0.0090 0.0126 1.0000
15.000 1.2302 0.05317 0.04792 0.0091 0.0126 1.0000
15.250 1.2363 0.05528 0.05010 0.0090 0.0124 1.0000
15.500 1.2428 0.05740 0.05228 0.0089 0.0121 1.0000
15.750 1.2460 0.05989 0.05484 0.0088 0.0121 1.0000
16.000 1.2517 0.06216 0.05717 0.0085 0.0119 1.0000
16.250 1.2553 0.06468 0.05976 0.0083 0.0117 1.0000
16.500 1.2598 0.06715 0.06229 0.0079 0.0116 1.0000
16.750 1.2613 0.07001 0.06523 0.0075 0.0114 1.0000
17.000 1.2645 0.07273 0.06801 0.0070 0.0113 1.0000
17.250 1.2674 0.07553 0.07087 0.0064 0.0112 1.0000
17.500 1.2696 0.07843 0.07385 0.0057 0.0111 1.0000
17.750 1.2740 0.08116 0.07663 0.0049 0.0109 1.0000
18.000 1.2740 0.08446 0.07999 0.0040 0.0107 1.0000
18.250 1.2738 0.08784 0.08344 0.0030 0.0106 1.0000
18.500 1.2746 0.09112 0.08678 0.0020 0.0105 1.0000
18.750 1.2720 0.09489 0.09063 0.0008 0.0104 1.0000
19.000 1.2695 0.09865 0.09446 -0.0004 0.0102 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 747A415 (naca747a415-il)