NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-015A AIRFOIL (n63015a-il) Reynolds number: 200,000 Max Cl/Cd: 46.56 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63015a-il-200000-n5.txt Download as CSV file: xf-n63015a-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9324 0.10856 0.10410 -0.0129 1.0000 0.0196
-16.500 -0.9626 0.09842 0.09371 -0.0189 1.0000 0.0195
-16.250 -0.9845 0.09057 0.08563 -0.0233 1.0000 0.0195
-16.000 -1.0018 0.08401 0.07887 -0.0266 1.0000 0.0195
-15.750 -1.0157 0.07832 0.07298 -0.0292 1.0000 0.0196
-15.500 -1.0271 0.07330 0.06778 -0.0313 1.0000 0.0197
-15.250 -1.0361 0.06885 0.06314 -0.0328 1.0000 0.0198
-15.000 -1.0431 0.06483 0.05894 -0.0340 1.0000 0.0199
-14.750 -1.0482 0.06120 0.05513 -0.0347 1.0000 0.0201
-14.500 -1.0513 0.05789 0.05165 -0.0353 1.0000 0.0203
-14.250 -1.0526 0.05485 0.04844 -0.0355 1.0000 0.0205
-14.000 -1.0520 0.05208 0.04550 -0.0356 1.0000 0.0207
-13.750 -1.0497 0.04953 0.04279 -0.0354 1.0000 0.0210
-13.500 -1.0458 0.04718 0.04027 -0.0351 1.0000 0.0213
-13.250 -1.0405 0.04503 0.03795 -0.0348 1.0000 0.0217
-13.000 -1.0339 0.04304 0.03579 -0.0343 1.0000 0.0220
-12.750 -1.0265 0.04115 0.03380 -0.0337 1.0000 0.0225
-12.500 -1.0186 0.03938 0.03200 -0.0331 1.0000 0.0229
-12.250 -1.0098 0.03774 0.03031 -0.0325 1.0000 0.0233
-12.000 -1.0004 0.03619 0.02869 -0.0318 1.0000 0.0238
-11.750 -0.9905 0.03468 0.02710 -0.0310 1.0000 0.0243
-11.500 -0.9802 0.03324 0.02557 -0.0301 1.0000 0.0249
-11.250 -0.9696 0.03184 0.02409 -0.0292 1.0000 0.0255
-11.000 -0.9588 0.03051 0.02267 -0.0282 1.0000 0.0261
-10.750 -0.9476 0.02927 0.02132 -0.0270 1.0000 0.0268
-10.500 -0.9382 0.02795 0.01996 -0.0257 1.0000 0.0275
-10.250 -0.9288 0.02673 0.01870 -0.0243 1.0000 0.0283
-10.000 -0.9180 0.02568 0.01761 -0.0228 1.0000 0.0293
-9.750 -0.9069 0.02472 0.01660 -0.0211 1.0000 0.0305
-9.500 -0.8956 0.02386 0.01567 -0.0193 1.0000 0.0319
-9.250 -0.8858 0.02302 0.01479 -0.0170 1.0000 0.0335
-9.000 -0.8760 0.02224 0.01401 -0.0147 1.0000 0.0355
-8.750 -0.8633 0.02157 0.01329 -0.0127 1.0000 0.0379
-8.500 -0.8512 0.02089 0.01258 -0.0105 1.0000 0.0406
-8.250 -0.8400 0.02024 0.01195 -0.0081 1.0000 0.0437
-8.000 -0.8283 0.01972 0.01139 -0.0056 1.0000 0.0474
-7.750 -0.8194 0.01916 0.01086 -0.0027 1.0000 0.0520
-7.500 -0.7885 0.01842 0.01015 -0.0042 0.9913 0.0614
-7.250 -0.7577 0.01770 0.00948 -0.0058 0.9811 0.0748
-7.000 -0.7277 0.01699 0.00883 -0.0070 0.9700 0.0927
-6.750 -0.6987 0.01626 0.00821 -0.0081 0.9583 0.1174
-6.500 -0.6716 0.01549 0.00760 -0.0088 0.9455 0.1507
-6.250 -0.6467 0.01471 0.00702 -0.0090 0.9315 0.1941
-6.000 -0.6242 0.01388 0.00644 -0.0087 0.9174 0.2503
-5.750 -0.6036 0.01310 0.00596 -0.0079 0.9032 0.3174
-5.500 -0.5825 0.01251 0.00563 -0.0069 0.8898 0.3823
-5.250 -0.5593 0.01216 0.00541 -0.0061 0.8776 0.4307
-5.000 -0.5351 0.01194 0.00524 -0.0054 0.8654 0.4646
-4.750 -0.5099 0.01180 0.00508 -0.0048 0.8538 0.4888
-4.500 -0.4843 0.01167 0.00492 -0.0043 0.8434 0.5081
-4.250 -0.4586 0.01158 0.00479 -0.0038 0.8328 0.5250
-4.000 -0.4328 0.01150 0.00468 -0.0033 0.8227 0.5421
-3.750 -0.4070 0.01144 0.00458 -0.0028 0.8136 0.5596
-3.500 -0.3810 0.01139 0.00451 -0.0023 0.8038 0.5749
-3.250 -0.3546 0.01136 0.00442 -0.0020 0.7954 0.5881
-3.000 -0.3280 0.01132 0.00433 -0.0017 0.7861 0.6005
-2.750 -0.3012 0.01129 0.00426 -0.0014 0.7782 0.6102
-2.500 -0.2741 0.01124 0.00418 -0.0012 0.7694 0.6191
-2.250 -0.2469 0.01121 0.00409 -0.0010 0.7618 0.6269
-2.000 -0.2196 0.01118 0.00401 -0.0009 0.7532 0.6345
-1.750 -0.1922 0.01115 0.00395 -0.0007 0.7461 0.6417
-1.500 -0.1648 0.01112 0.00388 -0.0006 0.7376 0.6494
-1.250 -0.1374 0.01110 0.00383 -0.0005 0.7306 0.6562
-1.000 -0.1100 0.01109 0.00379 -0.0004 0.7225 0.6642
-0.750 -0.0825 0.01107 0.00376 -0.0003 0.7153 0.6707
-0.500 -0.0550 0.01106 0.00374 -0.0002 0.7076 0.6785
-0.250 -0.0275 0.01105 0.00373 -0.0001 0.7002 0.6853
0.000 0.0000 0.01105 0.00373 0.0000 0.6929 0.6929
0.250 0.0275 0.01105 0.00373 0.0001 0.6853 0.7002
0.500 0.0550 0.01106 0.00374 0.0002 0.6785 0.7075
0.750 0.0825 0.01107 0.00376 0.0003 0.6707 0.7153
1.000 0.1100 0.01109 0.00379 0.0004 0.6642 0.7225
1.250 0.1374 0.01110 0.00384 0.0005 0.6562 0.7307
1.500 0.1648 0.01112 0.00388 0.0006 0.6494 0.7376
1.750 0.1922 0.01115 0.00395 0.0007 0.6417 0.7462
2.000 0.2196 0.01118 0.00401 0.0009 0.6345 0.7532
2.250 0.2469 0.01121 0.00409 0.0010 0.6269 0.7618
2.500 0.2741 0.01124 0.00418 0.0012 0.6191 0.7694
2.750 0.3012 0.01129 0.00426 0.0014 0.6102 0.7782
3.000 0.3280 0.01132 0.00433 0.0017 0.6004 0.7861
3.250 0.3546 0.01136 0.00442 0.0020 0.5881 0.7954
3.500 0.3810 0.01139 0.00451 0.0023 0.5750 0.8038
3.750 0.4070 0.01144 0.00458 0.0028 0.5596 0.8136
4.000 0.4328 0.01150 0.00468 0.0033 0.5421 0.8228
4.250 0.4586 0.01158 0.00479 0.0038 0.5250 0.8328
4.500 0.4843 0.01167 0.00492 0.0043 0.5081 0.8434
4.750 0.5099 0.01180 0.00508 0.0048 0.4889 0.8539
5.000 0.5351 0.01194 0.00524 0.0054 0.4646 0.8654
5.250 0.5593 0.01216 0.00541 0.0061 0.4306 0.8776
5.500 0.5825 0.01251 0.00563 0.0069 0.3822 0.8898
5.750 0.6036 0.01310 0.00596 0.0079 0.3174 0.9032
6.000 0.6242 0.01388 0.00644 0.0087 0.2503 0.9174
6.250 0.6467 0.01471 0.00702 0.0090 0.1940 0.9316
6.500 0.6716 0.01549 0.00760 0.0088 0.1506 0.9455
6.750 0.6987 0.01626 0.00821 0.0081 0.1174 0.9583
7.000 0.7277 0.01699 0.00883 0.0070 0.0927 0.9700
7.250 0.7578 0.01770 0.00948 0.0057 0.0748 0.9811
7.500 0.7886 0.01842 0.01015 0.0042 0.0614 0.9914
7.750 0.8194 0.01915 0.01086 0.0027 0.0520 1.0000
8.000 0.8284 0.01972 0.01138 0.0056 0.0474 1.0000
8.250 0.8400 0.02024 0.01195 0.0080 0.0437 1.0000
8.500 0.8513 0.02089 0.01258 0.0104 0.0406 1.0000
8.750 0.8634 0.02156 0.01329 0.0127 0.0379 1.0000
9.000 0.8761 0.02224 0.01400 0.0147 0.0355 1.0000
9.250 0.8860 0.02302 0.01479 0.0170 0.0335 1.0000
9.500 0.8958 0.02386 0.01567 0.0192 0.0319 1.0000
9.750 0.9072 0.02472 0.01660 0.0211 0.0305 1.0000
10.000 0.9184 0.02568 0.01761 0.0227 0.0293 1.0000
10.250 0.9292 0.02673 0.01870 0.0242 0.0283 1.0000
10.500 0.9387 0.02794 0.01995 0.0256 0.0275 1.0000
10.750 0.9481 0.02926 0.02132 0.0270 0.0268 1.0000
11.000 0.9594 0.03051 0.02266 0.0281 0.0261 1.0000
11.250 0.9703 0.03184 0.02408 0.0291 0.0255 1.0000
11.500 0.9809 0.03323 0.02556 0.0300 0.0249 1.0000
11.750 0.9912 0.03467 0.02709 0.0309 0.0243 1.0000
12.000 1.0012 0.03617 0.02867 0.0317 0.0238 1.0000
12.250 1.0107 0.03773 0.03029 0.0324 0.0233 1.0000
12.500 1.0195 0.03937 0.03198 0.0330 0.0229 1.0000
12.750 1.0274 0.04113 0.03378 0.0336 0.0224 1.0000
13.000 1.0349 0.04303 0.03577 0.0342 0.0220 1.0000
13.250 1.0416 0.04501 0.03793 0.0346 0.0216 1.0000
13.500 1.0469 0.04717 0.04025 0.0350 0.0213 1.0000
13.750 1.0508 0.04951 0.04277 0.0353 0.0210 1.0000
14.000 1.0532 0.05206 0.04548 0.0354 0.0207 1.0000
14.250 1.0539 0.05483 0.04842 0.0354 0.0205 1.0000
14.500 1.0527 0.05787 0.05163 0.0351 0.0203 1.0000
14.750 1.0496 0.06118 0.05512 0.0346 0.0201 1.0000
15.000 1.0445 0.06481 0.05892 0.0338 0.0199 1.0000
15.250 1.0376 0.06883 0.06312 0.0326 0.0198 1.0000
15.500 1.0286 0.07328 0.06775 0.0310 0.0197 1.0000
15.750 1.0173 0.07829 0.07296 0.0290 0.0196 1.0000
16.000 1.0034 0.08400 0.07886 0.0263 0.0195 1.0000
16.250 0.9862 0.09056 0.08563 0.0230 0.0195 1.0000
16.500 0.9642 0.09844 0.09373 0.0186 0.0195 1.0000
16.750 0.9338 0.10864 0.10419 0.0126 0.0196 1.0000
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Polar data table (+)
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