NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-015A AIRFOIL (n63015a-il) Reynolds number: 500,000 Max Cl/Cd: 66.32 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63015a-il-500000.txt Download as CSV file: xf-n63015a-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-015A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9395 0.12838 0.12551 -0.0006 1.0000 0.0181
-17.750 -0.9735 0.11666 0.11362 -0.0076 1.0000 0.0180
-17.500 -1.0019 0.10682 0.10360 -0.0134 1.0000 0.0179
-17.250 -1.0264 0.09821 0.09480 -0.0184 1.0000 0.0179
-17.000 -1.0482 0.09055 0.08696 -0.0227 1.0000 0.0179
-16.750 -1.0675 0.08377 0.07999 -0.0262 1.0000 0.0179
-16.500 -1.0844 0.07771 0.07375 -0.0291 1.0000 0.0179
-16.250 -1.0990 0.07233 0.06818 -0.0315 1.0000 0.0179
-16.000 -1.1118 0.06754 0.06320 -0.0334 1.0000 0.0180
-15.750 -1.1228 0.06323 0.05871 -0.0348 1.0000 0.0180
-15.500 -1.1322 0.05937 0.05468 -0.0358 1.0000 0.0181
-15.250 -1.1424 0.05517 0.05028 -0.0360 1.0000 0.0182
-15.000 -1.1466 0.05172 0.04667 -0.0357 1.0000 0.0184
-14.750 -1.1464 0.04888 0.04372 -0.0354 1.0000 0.0185
-14.500 -1.1435 0.04644 0.04118 -0.0350 1.0000 0.0187
-14.250 -1.1392 0.04424 0.03889 -0.0347 1.0000 0.0189
-14.000 -1.1339 0.04219 0.03676 -0.0342 1.0000 0.0191
-13.750 -1.1275 0.04027 0.03475 -0.0338 1.0000 0.0193
-13.500 -1.1203 0.03846 0.03285 -0.0332 1.0000 0.0196
-13.250 -1.1122 0.03673 0.03104 -0.0326 1.0000 0.0199
-13.000 -1.1032 0.03511 0.02932 -0.0319 1.0000 0.0201
-12.750 -1.0933 0.03359 0.02771 -0.0311 1.0000 0.0205
-12.500 -1.0827 0.03213 0.02616 -0.0302 1.0000 0.0208
-12.250 -1.0714 0.03079 0.02472 -0.0294 1.0000 0.0212
-12.000 -1.0592 0.02956 0.02340 -0.0286 1.0000 0.0216
-11.750 -1.0462 0.02847 0.02220 -0.0277 1.0000 0.0219
-11.500 -1.0366 0.02686 0.02053 -0.0263 1.0000 0.0224
-11.250 -1.0269 0.02545 0.01910 -0.0250 1.0000 0.0229
-11.000 -1.0153 0.02432 0.01793 -0.0237 1.0000 0.0233
-10.750 -1.0029 0.02331 0.01689 -0.0224 1.0000 0.0239
-10.500 -0.9901 0.02238 0.01592 -0.0210 1.0000 0.0244
-10.250 -0.9772 0.02151 0.01500 -0.0195 1.0000 0.0251
-10.000 -0.9641 0.02072 0.01415 -0.0178 1.0000 0.0258
-9.750 -0.9502 0.02006 0.01341 -0.0160 1.0000 0.0264
-9.500 -0.9445 0.01905 0.01238 -0.0129 1.0000 0.0272
-9.250 -0.9336 0.01829 0.01162 -0.0105 1.0000 0.0283
-9.000 -0.9195 0.01774 0.01105 -0.0085 1.0000 0.0296
-8.750 -0.9057 0.01726 0.01054 -0.0063 1.0000 0.0310
-8.500 -0.8965 0.01667 0.00992 -0.0032 1.0000 0.0326
-8.250 -0.8896 0.01614 0.00940 0.0003 1.0000 0.0345
-8.000 -0.8665 0.01566 0.00889 0.0006 0.9977 0.0374
-7.750 -0.8318 0.01487 0.00813 -0.0017 0.9930 0.0430
-7.500 -0.7975 0.01419 0.00748 -0.0037 0.9869 0.0511
-7.250 -0.7622 0.01355 0.00691 -0.0059 0.9814 0.0638
-7.000 -0.7305 0.01288 0.00635 -0.0074 0.9721 0.0835
-6.750 -0.7008 0.01225 0.00585 -0.0083 0.9606 0.1086
-6.500 -0.6736 0.01164 0.00539 -0.0087 0.9473 0.1412
-6.250 -0.6507 0.01098 0.00492 -0.0082 0.9316 0.1856
-6.000 -0.6309 0.01026 0.00445 -0.0070 0.9150 0.2434
-5.750 -0.6128 0.00950 0.00401 -0.0055 0.8990 0.3175
-5.500 -0.5929 0.00894 0.00370 -0.0043 0.8846 0.3864
-5.250 -0.5701 0.00863 0.00349 -0.0034 0.8717 0.4323
-5.000 -0.5456 0.00845 0.00334 -0.0027 0.8593 0.4617
-4.750 -0.5200 0.00832 0.00322 -0.0023 0.8476 0.4840
-4.500 -0.4942 0.00822 0.00310 -0.0018 0.8372 0.5040
-4.250 -0.4681 0.00815 0.00301 -0.0015 0.8268 0.5229
-4.000 -0.4415 0.00809 0.00293 -0.0012 0.8170 0.5382
-3.750 -0.4147 0.00805 0.00283 -0.0010 0.8079 0.5505
-3.500 -0.3873 0.00802 0.00276 -0.0008 0.7986 0.5621
-3.250 -0.3604 0.00799 0.00269 -0.0006 0.7903 0.5735
-3.000 -0.3333 0.00794 0.00265 -0.0004 0.7813 0.5863
-2.750 -0.3061 0.00794 0.00260 -0.0003 0.7736 0.5983
-2.500 -0.2785 0.00793 0.00256 -0.0002 0.7649 0.6094
-2.000 -0.2235 0.00788 0.00250 0.0000 0.7491 0.6286
-1.750 -0.1959 0.00788 0.00246 0.0001 0.7417 0.6374
-1.500 -0.1679 0.00785 0.00243 0.0001 0.7337 0.6450
-1.250 -0.1400 0.00784 0.00240 0.0001 0.7263 0.6524
-1.000 -0.1120 0.00783 0.00236 0.0001 0.7187 0.6599
-0.750 -0.0841 0.00781 0.00235 0.0001 0.7111 0.6670
-0.250 -0.0280 0.00779 0.00233 0.0000 0.6962 0.6815
0.000 0.0000 0.00783 0.00231 0.0000 0.6893 0.6893
0.250 0.0280 0.00779 0.00233 0.0000 0.6815 0.6962
0.750 0.0841 0.00781 0.00235 -0.0001 0.6670 0.7111
1.000 0.1120 0.00783 0.00236 -0.0001 0.6599 0.7188
1.250 0.1400 0.00784 0.00240 -0.0001 0.6524 0.7263
1.500 0.1679 0.00785 0.00243 -0.0001 0.6450 0.7337
1.750 0.1959 0.00788 0.00246 -0.0001 0.6373 0.7417
2.000 0.2235 0.00788 0.00250 0.0000 0.6286 0.7491
2.500 0.2785 0.00793 0.00256 0.0002 0.6094 0.7649
2.750 0.3061 0.00794 0.00260 0.0003 0.5984 0.7736
3.000 0.3333 0.00794 0.00265 0.0004 0.5863 0.7813
3.250 0.3604 0.00799 0.00269 0.0006 0.5735 0.7903
3.500 0.3873 0.00802 0.00276 0.0008 0.5622 0.7986
3.750 0.4147 0.00805 0.00283 0.0010 0.5505 0.8079
4.000 0.4416 0.00809 0.00293 0.0012 0.5382 0.8170
4.250 0.4682 0.00815 0.00301 0.0015 0.5229 0.8268
4.500 0.4942 0.00822 0.00310 0.0018 0.5039 0.8372
4.750 0.5200 0.00832 0.00322 0.0023 0.4841 0.8476
5.000 0.5456 0.00845 0.00334 0.0027 0.4617 0.8592
5.250 0.5701 0.00863 0.00349 0.0033 0.4323 0.8716
5.500 0.5929 0.00894 0.00370 0.0043 0.3863 0.8846
5.750 0.6128 0.00950 0.00401 0.0055 0.3173 0.8991
6.000 0.6309 0.01026 0.00446 0.0070 0.2432 0.9151
6.250 0.6507 0.01098 0.00492 0.0082 0.1853 0.9316
6.500 0.6736 0.01164 0.00539 0.0087 0.1411 0.9473
6.750 0.7009 0.01225 0.00585 0.0083 0.1085 0.9606
7.000 0.7306 0.01288 0.00635 0.0073 0.0835 0.9721
7.250 0.7623 0.01355 0.00691 0.0059 0.0638 0.9815
7.500 0.7976 0.01418 0.00748 0.0037 0.0511 0.9870
7.750 0.8319 0.01487 0.00813 0.0017 0.0430 0.9931
8.000 0.8667 0.01566 0.00889 -0.0006 0.0374 0.9977
8.250 0.8895 0.01614 0.00940 -0.0002 0.0345 1.0000
8.500 0.8965 0.01667 0.00992 0.0032 0.0326 1.0000
8.750 0.9057 0.01726 0.01054 0.0063 0.0310 1.0000
9.000 0.9196 0.01774 0.01105 0.0085 0.0296 1.0000
9.250 0.9338 0.01829 0.01162 0.0105 0.0283 1.0000
9.500 0.9449 0.01906 0.01238 0.0128 0.0272 1.0000
9.750 0.9507 0.02006 0.01342 0.0159 0.0264 1.0000
10.000 0.9646 0.02073 0.01415 0.0177 0.0258 1.0000
10.250 0.9778 0.02151 0.01500 0.0193 0.0251 1.0000
10.500 0.9908 0.02238 0.01592 0.0209 0.0244 1.0000
10.750 1.0037 0.02332 0.01690 0.0223 0.0239 1.0000
11.000 1.0162 0.02432 0.01793 0.0235 0.0233 1.0000
11.250 1.0278 0.02546 0.01910 0.0248 0.0228 1.0000
11.500 1.0376 0.02686 0.02054 0.0261 0.0224 1.0000
11.750 1.0473 0.02846 0.02219 0.0275 0.0219 1.0000
12.000 1.0604 0.02956 0.02340 0.0284 0.0216 1.0000
12.250 1.0726 0.03078 0.02471 0.0292 0.0212 1.0000
12.500 1.0839 0.03213 0.02615 0.0301 0.0208 1.0000
12.750 1.0946 0.03358 0.02770 0.0309 0.0205 1.0000
13.000 1.1046 0.03510 0.02931 0.0317 0.0201 1.0000
13.250 1.1136 0.03673 0.03103 0.0324 0.0199 1.0000
13.500 1.1217 0.03844 0.03284 0.0330 0.0196 1.0000
13.750 1.1290 0.04026 0.03474 0.0335 0.0193 1.0000
14.000 1.1354 0.04218 0.03674 0.0340 0.0191 1.0000
14.250 1.1408 0.04422 0.03887 0.0344 0.0189 1.0000
14.500 1.1452 0.04642 0.04116 0.0348 0.0187 1.0000
14.750 1.1481 0.04887 0.04371 0.0352 0.0185 1.0000
15.000 1.1483 0.05171 0.04666 0.0355 0.0184 1.0000
15.250 1.1440 0.05517 0.05028 0.0357 0.0182 1.0000
15.500 1.1338 0.05939 0.05469 0.0355 0.0181 1.0000
15.750 1.1244 0.06324 0.05873 0.0345 0.0180 1.0000
16.000 1.1134 0.06755 0.06322 0.0331 0.0180 1.0000
16.250 1.1006 0.07237 0.06822 0.0312 0.0179 1.0000
16.500 1.0859 0.07776 0.07380 0.0288 0.0179 1.0000
16.750 1.0690 0.08386 0.08008 0.0258 0.0178 1.0000
17.000 1.0496 0.09067 0.08709 0.0222 0.0178 1.0000
17.250 1.0280 0.09831 0.09491 0.0180 0.0179 1.0000
17.500 1.0031 0.10703 0.10381 0.0129 0.0179 1.0000
17.750 0.9743 0.11699 0.11395 0.0070 0.0180 1.0000
18.000 0.9401 0.12880 0.12594 0.0000 0.0181 1.0000
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