NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16-015 (naca16015-il) Reynolds number: 200,000 Max Cl/Cd: 31.97 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16015-il-200000-n5.txt Download as CSV file: xf-naca16015-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-015
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8149 0.08435 0.08025 -0.0675 1.0000 0.0155
-15.000 -0.8570 0.07531 0.07097 -0.0704 1.0000 0.0153
-14.750 -0.8887 0.06922 0.06466 -0.0705 1.0000 0.0153
-14.500 -0.9149 0.06454 0.05978 -0.0692 1.0000 0.0153
-14.250 -0.9378 0.06068 0.05572 -0.0669 1.0000 0.0154
-14.000 -0.9579 0.05740 0.05225 -0.0640 1.0000 0.0156
-13.750 -0.9759 0.05450 0.04915 -0.0606 1.0000 0.0157
-13.500 -0.9919 0.05194 0.04638 -0.0567 1.0000 0.0159
-13.250 -1.0057 0.04964 0.04388 -0.0526 1.0000 0.0162
-13.000 -1.0177 0.04754 0.04156 -0.0484 1.0000 0.0166
-12.750 -1.0280 0.04556 0.03934 -0.0439 1.0000 0.0170
-12.500 -1.0362 0.04368 0.03719 -0.0395 1.0000 0.0176
-12.250 -1.0346 0.04168 0.03483 -0.0367 0.9991 0.0181
-12.000 -1.0263 0.04007 0.03313 -0.0353 0.9976 0.0187
-11.750 -1.0153 0.03893 0.03190 -0.0340 0.9960 0.0194
-11.500 -1.0025 0.03774 0.03057 -0.0329 0.9946 0.0201
-11.250 -0.9890 0.03645 0.02910 -0.0316 0.9928 0.0209
-11.000 -0.9735 0.03514 0.02758 -0.0305 0.9909 0.0221
-10.750 -0.9560 0.03399 0.02615 -0.0296 0.9891 0.0235
-10.500 -0.9381 0.03275 0.02477 -0.0290 0.9877 0.0247
-10.250 -0.9198 0.03190 0.02387 -0.0284 0.9862 0.0259
-10.000 -0.8985 0.03103 0.02289 -0.0282 0.9851 0.0274
-9.750 -0.8805 0.03019 0.02192 -0.0271 0.9827 0.0290
-9.500 -0.8605 0.02950 0.02102 -0.0262 0.9804 0.0307
-9.250 -0.8404 0.02841 0.01992 -0.0257 0.9787 0.0325
-9.000 -0.8196 0.02771 0.01915 -0.0252 0.9771 0.0342
-8.750 -0.7964 0.02707 0.01844 -0.0252 0.9757 0.0364
-8.500 -0.7713 0.02645 0.01768 -0.0254 0.9746 0.0386
-8.250 -0.7559 0.02573 0.01690 -0.0235 0.9714 0.0402
-8.000 -0.7397 0.02503 0.01620 -0.0220 0.9687 0.0424
-7.750 -0.7194 0.02449 0.01560 -0.0212 0.9666 0.0448
-7.500 -0.6967 0.02394 0.01497 -0.0208 0.9648 0.0471
-7.250 -0.6720 0.02345 0.01438 -0.0209 0.9634 0.0494
-7.000 -0.6568 0.02283 0.01376 -0.0190 0.9606 0.0524
-6.750 -0.6452 0.02241 0.01332 -0.0161 0.9566 0.0550
-6.500 -0.6256 0.02198 0.01281 -0.0150 0.9540 0.0584
-6.250 -0.6033 0.02151 0.01231 -0.0144 0.9520 0.0632
-6.000 -0.5796 0.02104 0.01185 -0.0142 0.9504 0.0717
-5.750 -0.5555 0.02056 0.01141 -0.0141 0.9491 0.0847
-5.500 -0.5558 0.02031 0.01120 -0.0084 0.9426 0.0957
-5.250 -0.5377 0.01986 0.01083 -0.0070 0.9397 0.1195
-5.000 -0.5184 0.01934 0.01046 -0.0058 0.9375 0.1556
-4.750 -0.4995 0.01873 0.01009 -0.0046 0.9358 0.2075
-4.500 -0.5020 0.01833 0.00989 0.0014 0.9295 0.2538
-4.250 -0.4973 0.01756 0.00950 0.0057 0.9253 0.3376
-3.750 -0.5022 0.01571 0.00876 0.0180 0.9166 0.5632
-3.500 -0.4360 0.01565 0.00963 0.0103 0.9208 0.7588
-3.250 -0.3863 0.01630 0.01032 0.0061 0.9209 0.8006
-3.000 -0.3798 0.01657 0.01056 0.0108 0.9150 0.8165
-2.750 -0.3595 0.01687 0.01082 0.0127 0.9116 0.8338
-2.500 -0.3028 0.01825 0.01216 0.0076 0.9123 0.8516
-2.250 -0.2755 0.01872 0.01258 0.0081 0.9101 0.8630
-2.000 -0.2329 0.01904 0.01283 0.0048 0.9094 0.8645
-1.750 -0.1932 0.01924 0.01297 0.0020 0.9085 0.8663
-1.250 -0.1509 0.01921 0.01286 0.0043 0.9024 0.8774
-1.000 -0.1202 0.01941 0.01303 0.0034 0.8991 0.8789
-0.750 -0.0861 0.01950 0.01309 0.0017 0.8970 0.8806
-0.500 -0.0521 0.01953 0.01311 0.0000 0.8952 0.8826
0.000 0.0000 0.01918 0.01272 0.0000 0.8916 0.8916
0.500 0.0521 0.01953 0.01311 0.0000 0.8826 0.8952
0.750 0.0862 0.01950 0.01309 -0.0017 0.8806 0.8970
1.000 0.1202 0.01941 0.01303 -0.0033 0.8789 0.8991
1.250 0.1507 0.01921 0.01285 -0.0042 0.8774 0.9025
1.750 0.1932 0.01924 0.01297 -0.0020 0.8663 0.9085
2.000 0.2329 0.01904 0.01283 -0.0048 0.8645 0.9095
2.250 0.2754 0.01872 0.01258 -0.0081 0.8630 0.9102
2.500 0.3028 0.01825 0.01216 -0.0076 0.8516 0.9124
2.750 0.3597 0.01686 0.01081 -0.0127 0.8338 0.9116
3.000 0.3799 0.01656 0.01055 -0.0108 0.8165 0.9150
3.250 0.3862 0.01630 0.01031 -0.0060 0.8003 0.9209
3.500 0.4362 0.01564 0.00962 -0.0104 0.7586 0.9208
3.750 0.5020 0.01570 0.00876 -0.0179 0.5634 0.9167
4.000 0.4944 0.01654 0.00903 -0.0105 0.4524 0.9222
4.250 0.4973 0.01756 0.00950 -0.0057 0.3373 0.9253
4.500 0.5021 0.01832 0.00988 -0.0015 0.2544 0.9296
4.750 0.4997 0.01873 0.01008 0.0046 0.2072 0.9358
5.000 0.5186 0.01934 0.01046 0.0057 0.1555 0.9376
5.250 0.5379 0.01985 0.01082 0.0069 0.1194 0.9397
5.500 0.5560 0.02031 0.01119 0.0084 0.0957 0.9426
5.750 0.5558 0.02056 0.01141 0.0140 0.0847 0.9491
6.000 0.5799 0.02103 0.01185 0.0141 0.0716 0.9504
6.250 0.6036 0.02151 0.01231 0.0144 0.0631 0.9520
6.500 0.6260 0.02197 0.01281 0.0149 0.0584 0.9540
6.750 0.6455 0.02240 0.01331 0.0161 0.0550 0.9567
7.000 0.6567 0.02281 0.01375 0.0190 0.0524 0.9607
7.250 0.6725 0.02345 0.01438 0.0208 0.0494 0.9634
7.500 0.6972 0.02393 0.01496 0.0207 0.0471 0.9649
7.750 0.7198 0.02448 0.01559 0.0211 0.0447 0.9666
8.000 0.7401 0.02502 0.01618 0.0219 0.0423 0.9687
8.250 0.7562 0.02572 0.01689 0.0235 0.0402 0.9715
8.500 0.7718 0.02644 0.01767 0.0253 0.0385 0.9746
8.750 0.7970 0.02706 0.01842 0.0250 0.0364 0.9758
9.000 0.8202 0.02770 0.01914 0.0251 0.0342 0.9772
9.250 0.8410 0.02840 0.01991 0.0256 0.0325 0.9788
9.500 0.8611 0.02949 0.02102 0.0261 0.0307 0.9805
9.750 0.8811 0.03019 0.02192 0.0269 0.0290 0.9828
10.000 0.8993 0.03102 0.02288 0.0280 0.0273 0.9851
10.250 0.9206 0.03189 0.02386 0.0282 0.0259 0.9863
10.500 0.9390 0.03275 0.02477 0.0288 0.0247 0.9877
10.750 0.9567 0.03396 0.02612 0.0295 0.0234 0.9892
11.000 0.9744 0.03514 0.02757 0.0304 0.0221 0.9910
11.250 0.9899 0.03644 0.02909 0.0315 0.0209 0.9929
11.500 1.0035 0.03774 0.03057 0.0327 0.0201 0.9947
11.750 1.0163 0.03891 0.03188 0.0338 0.0193 0.9961
12.000 1.0274 0.04006 0.03312 0.0351 0.0187 0.9977
12.250 1.0358 0.04168 0.03483 0.0365 0.0181 0.9992
12.500 1.0365 0.04366 0.03717 0.0394 0.0176 1.0000
12.750 1.0283 0.04553 0.03931 0.0439 0.0170 1.0000
13.000 1.0181 0.04751 0.04153 0.0483 0.0166 1.0000
13.250 1.0061 0.04962 0.04385 0.0526 0.0162 1.0000
13.500 0.9924 0.05189 0.04633 0.0567 0.0159 1.0000
13.750 0.9763 0.05447 0.04912 0.0606 0.0157 1.0000
14.000 0.9586 0.05732 0.05216 0.0640 0.0155 1.0000
14.250 0.9385 0.06060 0.05564 0.0669 0.0154 1.0000
14.500 0.9161 0.06439 0.05962 0.0692 0.0153 1.0000
14.750 0.8895 0.06911 0.06455 0.0705 0.0153 1.0000
15.000 0.8572 0.07531 0.07097 0.0703 0.0153 1.0000
15.250 0.8158 0.08422 0.08012 0.0675 0.0155 1.0000
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