NACA 6-H-15 AIRFOIL (n6h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 6-H-15 AIRFOIL (n6h15-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.89 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n6h15-il-1000000-n5.txt Download as CSV file: xf-n6h15-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6-H-15 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -1.0699 0.03610 0.03212 -0.0315 0.6200 0.0068
-13.500 -1.0783 0.03257 0.02830 -0.0276 0.6180 0.0068
-13.250 -1.0747 0.03032 0.02585 -0.0249 0.6157 0.0069
-13.000 -1.0660 0.02853 0.02386 -0.0226 0.6134 0.0070
-12.750 -1.0540 0.02707 0.02224 -0.0206 0.6110 0.0072
-12.500 -1.0393 0.02584 0.02086 -0.0190 0.6088 0.0074
-12.250 -1.0232 0.02471 0.01960 -0.0175 0.6069 0.0076
-12.000 -1.0056 0.02371 0.01847 -0.0161 0.6049 0.0077
-11.750 -0.9869 0.02278 0.01742 -0.0148 0.6025 0.0079
-11.500 -0.9673 0.02190 0.01641 -0.0137 0.6001 0.0081
-11.250 -0.9467 0.02112 0.01548 -0.0127 0.5974 0.0082
-11.000 -0.9255 0.02037 0.01460 -0.0118 0.5949 0.0084
-10.750 -0.9031 0.01973 0.01384 -0.0110 0.5925 0.0086
-10.500 -0.8809 0.01897 0.01299 -0.0102 0.5908 0.0089
-10.250 -0.8577 0.01831 0.01225 -0.0095 0.5888 0.0092
-10.000 -0.8336 0.01779 0.01167 -0.0090 0.5867 0.0096
-9.750 -0.8093 0.01729 0.01110 -0.0085 0.5845 0.0100
-9.500 -0.7846 0.01681 0.01054 -0.0081 0.5823 0.0104
-9.250 -0.7596 0.01635 0.00999 -0.0077 0.5802 0.0108
-9.000 -0.7344 0.01591 0.00946 -0.0073 0.5781 0.0111
-8.750 -0.7090 0.01546 0.00894 -0.0069 0.5764 0.0114
-8.500 -0.6831 0.01508 0.00853 -0.0067 0.5747 0.0121
-8.250 -0.6569 0.01476 0.00817 -0.0064 0.5728 0.0126
-8.000 -0.6308 0.01444 0.00782 -0.0062 0.5706 0.0132
-7.750 -0.6045 0.01413 0.00744 -0.0060 0.5685 0.0138
-7.500 -0.5782 0.01382 0.00707 -0.0058 0.5663 0.0144
-7.250 -0.5515 0.01362 0.00686 -0.0056 0.5643 0.0152
-7.000 -0.5247 0.01347 0.00670 -0.0055 0.5623 0.0161
-6.750 -0.4979 0.01326 0.00645 -0.0054 0.5609 0.0168
-6.500 -0.4711 0.01303 0.00619 -0.0052 0.5595 0.0175
-6.250 -0.4443 0.01280 0.00590 -0.0051 0.5579 0.0180
-6.000 -0.4175 0.01259 0.00570 -0.0050 0.5562 0.0188
-5.750 -0.3904 0.01247 0.00557 -0.0049 0.5545 0.0195
-5.500 -0.3633 0.01232 0.00540 -0.0048 0.5528 0.0202
-5.250 -0.3363 0.01217 0.00522 -0.0047 0.5510 0.0210
-5.000 -0.3093 0.01199 0.00500 -0.0046 0.5491 0.0217
-4.500 -0.2556 0.01158 0.00453 -0.0044 0.5456 0.0230
-4.250 -0.2289 0.01135 0.00430 -0.0043 0.5438 0.0236
-4.000 -0.2018 0.01120 0.00414 -0.0042 0.5424 0.0244
-3.750 -0.1749 0.01104 0.00398 -0.0041 0.5409 0.0251
-3.500 -0.1480 0.01088 0.00380 -0.0040 0.5393 0.0258
-3.250 -0.1212 0.01071 0.00361 -0.0039 0.5376 0.0264
-3.000 -0.0943 0.01059 0.00346 -0.0038 0.5357 0.0271
-2.750 -0.0675 0.01046 0.00330 -0.0037 0.5338 0.0275
-2.500 -0.0409 0.01032 0.00314 -0.0036 0.5319 0.0278
-2.250 -0.0149 0.01010 0.00290 -0.0033 0.5308 0.0289
-2.000 0.0116 0.00994 0.00276 -0.0031 0.5297 0.0299
-1.750 0.0383 0.00982 0.00264 -0.0030 0.5287 0.0307
-1.500 0.0650 0.00971 0.00253 -0.0029 0.5275 0.0316
-1.250 0.0919 0.00961 0.00243 -0.0028 0.5262 0.0324
-1.000 0.1187 0.00952 0.00234 -0.0027 0.5250 0.0332
-0.750 0.1456 0.00945 0.00226 -0.0026 0.5237 0.0341
-0.500 0.1724 0.00938 0.00219 -0.0026 0.5224 0.0355
-0.250 0.1991 0.00930 0.00213 -0.0025 0.5211 0.0388
0.000 0.2258 0.00923 0.00208 -0.0024 0.5197 0.0440
0.250 0.2512 0.00910 0.00205 -0.0021 0.5183 0.0737
0.500 0.2769 0.00900 0.00204 -0.0018 0.5169 0.1048
0.750 0.3027 0.00891 0.00203 -0.0016 0.5158 0.1325
1.000 0.3267 0.00871 0.00202 -0.0011 0.5147 0.1960
1.250 0.3283 0.00764 0.00191 0.0038 0.5136 0.5270
1.500 0.3177 0.00655 0.00184 0.0120 0.5125 0.8370
1.750 0.3443 0.00662 0.00193 0.0121 0.5113 0.8539
2.000 0.3707 0.00672 0.00203 0.0124 0.5102 0.8664
2.250 0.3989 0.00682 0.00216 0.0123 0.5090 0.8741
2.500 0.4265 0.00690 0.00223 0.0122 0.5077 0.8784
2.750 0.4539 0.00697 0.00228 0.0121 0.5060 0.8810
3.000 0.4824 0.00706 0.00237 0.0118 0.5026 0.8857
3.250 0.5108 0.00711 0.00244 0.0114 0.4989 0.8877
3.500 0.5392 0.00716 0.00249 0.0111 0.4957 0.8894
3.750 0.5673 0.00723 0.00256 0.0108 0.4928 0.8914
4.000 0.5950 0.00730 0.00261 0.0105 0.4892 0.8927
4.250 0.6228 0.00736 0.00266 0.0102 0.4858 0.8929
4.500 0.6510 0.00739 0.00270 0.0098 0.4815 0.8932
4.750 0.6787 0.00746 0.00276 0.0095 0.4755 0.8935
5.000 0.7059 0.00754 0.00283 0.0092 0.4679 0.8938
5.250 0.7328 0.00765 0.00291 0.0090 0.4590 0.8941
5.500 0.7596 0.00776 0.00301 0.0087 0.4495 0.8944
5.750 0.7836 0.00801 0.00317 0.0089 0.4276 0.8948
6.000 0.7894 0.00917 0.00395 0.0118 0.3489 0.8957
6.250 0.8038 0.00977 0.00444 0.0134 0.3250 0.8963
6.500 0.8204 0.01021 0.00483 0.0147 0.3101 0.8973
6.750 0.8339 0.01069 0.00527 0.0165 0.2935 0.8985
7.000 0.8219 0.01167 0.00614 0.0224 0.2542 0.9011
7.250 0.7907 0.01401 0.00834 0.0294 0.2138 0.9046
7.500 0.7806 0.01580 0.01006 0.0332 0.1924 0.9070
7.750 0.7752 0.01743 0.01162 0.0364 0.1711 0.9092
8.000 0.7699 0.01909 0.01319 0.0394 0.1478 0.9111
8.250 0.7449 0.02193 0.01579 0.0438 0.0924 0.9144
8.500 0.7473 0.02340 0.01722 0.0455 0.0761 0.9167
8.750 0.7567 0.02447 0.01829 0.0466 0.0696 0.9186
9.000 0.7684 0.02546 0.01929 0.0474 0.0659 0.9206
9.250 0.7820 0.02636 0.02021 0.0479 0.0640 0.9225
9.500 0.7939 0.02741 0.02127 0.0485 0.0612 0.9247
9.750 0.8064 0.02845 0.02233 0.0490 0.0590 0.9268
10.250 0.8363 0.03051 0.02445 0.0491 0.0560 0.9319
10.500 0.8533 0.03157 0.02556 0.0486 0.0549 0.9350
10.750 0.8723 0.03255 0.02659 0.0479 0.0545 0.9380
11.000 0.8921 0.03357 0.02766 0.0469 0.0532 0.9411
11.250 0.9116 0.03475 0.02888 0.0457 0.0521 0.9443
11.500 0.9337 0.03596 0.03013 0.0439 0.0511 0.9473
11.750 0.9569 0.03720 0.03142 0.0418 0.0499 0.9502
12.000 0.9782 0.03870 0.03293 0.0396 0.0475 0.9532
12.250 1.0001 0.04017 0.03443 0.0374 0.0465 0.9559
12.500 1.0219 0.04167 0.03598 0.0351 0.0446 0.9583
13.000 1.0690 0.04430 0.03871 0.0306 0.0429 0.9631
13.250 1.0906 0.04576 0.04021 0.0285 0.0417 0.9662
13.500 1.1110 0.04728 0.04176 0.0265 0.0397 0.9699
13.750 1.1299 0.04889 0.04337 0.0246 0.0370 0.9741
14.000 1.1487 0.05047 0.04499 0.0229 0.0349 0.9792
14.250 1.1644 0.05225 0.04675 0.0213 0.0303 0.9874
14.750 1.1732 0.05673 0.05110 0.0218 0.0151 1.0000
15.000 1.1777 0.05871 0.05311 0.0222 0.0131 1.0000
15.250 1.1847 0.06044 0.05487 0.0224 0.0119 1.0000
15.500 1.1913 0.06225 0.05672 0.0227 0.0110 1.0000
15.750 1.1956 0.06433 0.05883 0.0229 0.0098 1.0000
16.000 1.2036 0.06605 0.06059 0.0230 0.0095 1.0000
16.250 1.2109 0.06785 0.06243 0.0231 0.0087 1.0000
16.500 1.2158 0.06993 0.06455 0.0232 0.0082 1.0000
16.750 1.2213 0.07196 0.06662 0.0233 0.0078 1.0000
17.000 1.2270 0.07397 0.06867 0.0233 0.0074 1.0000
17.250 1.2330 0.07603 0.07079 0.0232 0.0072 1.0000
17.500 1.2390 0.07809 0.07290 0.0231 0.0069 1.0000
17.750 1.2446 0.08018 0.07503 0.0229 0.0066 1.0000
18.000 1.2490 0.08242 0.07733 0.0228 0.0064 1.0000
18.250 1.2528 0.08478 0.07973 0.0225 0.0060 1.0000
18.500 1.2573 0.08706 0.08206 0.0222 0.0058 1.0000
18.750 1.2590 0.08972 0.08477 0.0219 0.0055 1.0000
19.000 1.2629 0.09215 0.08728 0.0215 0.0053 1.0000
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