NACA 16-012 (naca16012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16-012 (naca16012-il) Reynolds number: 1,000,000 Max Cl/Cd: 51.69 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16012-il-1000000.txt Download as CSV file: xf-naca16012-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-012
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 -0.9473 0.06052 0.05829 -0.0662 1.0000 0.0066
-14.750 -0.9821 0.05354 0.05109 -0.0674 1.0000 0.0066
-14.500 -1.0072 0.04896 0.04634 -0.0662 1.0000 0.0066
-14.250 -1.0302 0.04526 0.04245 -0.0636 1.0000 0.0066
-14.000 -1.0484 0.04247 0.03951 -0.0601 1.0000 0.0066
-13.750 -1.0624 0.04034 0.03727 -0.0562 1.0000 0.0066
-13.500 -1.0763 0.03844 0.03523 -0.0517 1.0000 0.0067
-13.250 -1.0890 0.03679 0.03347 -0.0468 1.0000 0.0068
-13.000 -1.0997 0.03542 0.03197 -0.0418 1.0000 0.0068
-12.750 -1.1100 0.03415 0.03059 -0.0365 1.0000 0.0069
-12.500 -1.1203 0.03296 0.02928 -0.0308 1.0000 0.0069
-12.250 -1.1131 0.03156 0.02773 -0.0288 0.9991 0.0071
-12.000 -1.1035 0.02992 0.02590 -0.0271 0.9978 0.0072
-11.750 -1.0914 0.02839 0.02420 -0.0257 0.9965 0.0074
-11.500 -1.0767 0.02702 0.02264 -0.0245 0.9954 0.0076
-11.250 -1.0600 0.02570 0.02114 -0.0236 0.9945 0.0078
-11.000 -1.0455 0.02455 0.01983 -0.0220 0.9927 0.0081
-10.750 -1.0283 0.02350 0.01863 -0.0207 0.9907 0.0083
-10.500 -1.0074 0.02267 0.01767 -0.0202 0.9891 0.0085
-10.250 -0.9848 0.02185 0.01672 -0.0199 0.9878 0.0087
-10.000 -0.9682 0.01966 0.01429 -0.0188 0.9868 0.0094
-9.750 -0.9422 0.01912 0.01370 -0.0192 0.9858 0.0099
-9.500 -0.9144 0.01867 0.01322 -0.0199 0.9851 0.0104
-9.250 -0.8864 0.01810 0.01258 -0.0206 0.9844 0.0110
-9.000 -0.8584 0.01749 0.01188 -0.0213 0.9839 0.0115
-8.750 -0.8381 0.01703 0.01136 -0.0202 0.9816 0.0118
-8.500 -0.8204 0.01613 0.01034 -0.0186 0.9788 0.0125
-8.250 -0.7970 0.01541 0.00958 -0.0182 0.9770 0.0134
-8.000 -0.7689 0.01506 0.00922 -0.0188 0.9758 0.0143
-7.750 -0.7404 0.01470 0.00884 -0.0195 0.9748 0.0153
-7.500 -0.7100 0.01446 0.00856 -0.0205 0.9741 0.0162
-7.250 -0.6834 0.01368 0.00773 -0.0208 0.9733 0.0180
-7.000 -0.6524 0.01337 0.00742 -0.0221 0.9727 0.0195
-6.750 -0.6210 0.01308 0.00712 -0.0233 0.9722 0.0211
-6.500 -0.5889 0.01292 0.00695 -0.0247 0.9718 0.0221
-6.250 -0.5620 0.01222 0.00621 -0.0250 0.9711 0.0254
-6.000 -0.5481 0.01206 0.00604 -0.0222 0.9663 0.0271
-5.750 -0.5221 0.01182 0.00578 -0.0221 0.9642 0.0288
-5.500 -0.4933 0.01163 0.00558 -0.0227 0.9628 0.0298
-5.250 -0.4673 0.01110 0.00500 -0.0226 0.9614 0.0339
-5.000 -0.4388 0.01081 0.00471 -0.0231 0.9603 0.0367
-4.750 -0.4098 0.01057 0.00445 -0.0237 0.9593 0.0389
-4.500 -0.3810 0.01028 0.00415 -0.0242 0.9582 0.0434
-4.250 -0.3545 0.01001 0.00391 -0.0242 0.9567 0.0522
-4.000 -0.3413 0.00967 0.00375 -0.0212 0.9517 0.0891
-3.750 -0.3215 0.00914 0.00350 -0.0199 0.9490 0.1576
-3.500 -0.3020 0.00848 0.00322 -0.0186 0.9468 0.2531
-3.250 -0.2854 0.00766 0.00290 -0.0166 0.9446 0.3871
-3.000 -0.2810 0.00693 0.00269 -0.0119 0.9397 0.5228
-2.750 -0.2785 0.00619 0.00246 -0.0064 0.9346 0.6530
-2.500 -0.2640 0.00572 0.00231 -0.0034 0.9320 0.7383
-2.250 -0.2403 0.00551 0.00225 -0.0024 0.9302 0.7853
-2.000 -0.2188 0.00545 0.00226 -0.0010 0.9272 0.8131
-1.750 -0.1961 0.00542 0.00226 0.0001 0.9238 0.8315
-1.500 -0.1696 0.00538 0.00225 0.0003 0.9213 0.8459
-1.250 -0.1418 0.00535 0.00223 0.0003 0.9193 0.8595
-1.000 -0.1129 0.00542 0.00237 0.0003 0.9176 0.8801
-0.750 -0.0829 0.00554 0.00250 0.0000 0.9160 0.8926
-0.500 -0.0601 0.00562 0.00260 0.0011 0.9125 0.9001
-0.250 -0.0316 0.00566 0.00265 0.0009 0.9095 0.9041
0.000 0.0000 0.00569 0.00268 0.0000 0.9069 0.9069
0.250 0.0316 0.00566 0.00264 -0.0009 0.9040 0.9095
0.500 0.0601 0.00562 0.00260 -0.0011 0.9001 0.9125
0.750 0.0829 0.00554 0.00250 0.0000 0.8926 0.9160
1.000 0.1129 0.00542 0.00237 -0.0003 0.8803 0.9176
1.250 0.1417 0.00535 0.00224 -0.0003 0.8598 0.9193
1.500 0.1695 0.00538 0.00225 -0.0003 0.8458 0.9213
1.750 0.1961 0.00542 0.00226 -0.0001 0.8316 0.9238
2.000 0.2187 0.00545 0.00226 0.0011 0.8128 0.9272
2.250 0.2404 0.00551 0.00225 0.0024 0.7856 0.9302
2.500 0.2640 0.00572 0.00231 0.0034 0.7385 0.9320
2.750 0.2785 0.00619 0.00246 0.0063 0.6530 0.9347
3.000 0.2811 0.00692 0.00269 0.0118 0.5235 0.9397
3.250 0.2854 0.00766 0.00290 0.0166 0.3865 0.9446
3.500 0.3020 0.00848 0.00322 0.0186 0.2529 0.9468
3.750 0.3215 0.00914 0.00350 0.0199 0.1574 0.9490
4.000 0.3413 0.00967 0.00375 0.0212 0.0889 0.9518
4.250 0.3546 0.01001 0.00391 0.0242 0.0521 0.9567
4.500 0.3810 0.01028 0.00415 0.0242 0.0433 0.9582
4.750 0.4099 0.01057 0.00445 0.0237 0.0389 0.9593
5.000 0.4390 0.01081 0.00471 0.0231 0.0366 0.9603
5.250 0.4675 0.01110 0.00500 0.0226 0.0338 0.9614
5.500 0.4935 0.01163 0.00558 0.0226 0.0298 0.9629
5.750 0.5221 0.01182 0.00578 0.0221 0.0288 0.9643
6.000 0.5480 0.01206 0.00604 0.0222 0.0271 0.9663
6.250 0.5621 0.01222 0.00621 0.0250 0.0254 0.9711
6.500 0.5891 0.01291 0.00694 0.0246 0.0221 0.9718
6.750 0.6213 0.01308 0.00712 0.0232 0.0211 0.9723
7.000 0.6527 0.01336 0.00742 0.0220 0.0195 0.9727
7.250 0.6837 0.01367 0.00772 0.0208 0.0180 0.9733
7.500 0.7105 0.01444 0.00854 0.0204 0.0162 0.9741
7.750 0.7406 0.01470 0.00884 0.0194 0.0153 0.9749
8.000 0.7691 0.01506 0.00923 0.0188 0.0143 0.9759
8.250 0.7971 0.01542 0.00959 0.0182 0.0135 0.9771
8.500 0.8207 0.01611 0.01033 0.0185 0.0125 0.9788
8.750 0.8380 0.01701 0.01134 0.0202 0.0118 0.9817
9.000 0.8588 0.01747 0.01187 0.0212 0.0115 0.9839
9.250 0.8869 0.01808 0.01256 0.0205 0.0109 0.9845
9.500 0.9148 0.01867 0.01322 0.0198 0.0104 0.9851
9.750 0.9426 0.01913 0.01371 0.0191 0.0099 0.9858
10.000 0.9687 0.01966 0.01429 0.0187 0.0094 0.9868
10.250 0.9846 0.02200 0.01689 0.0199 0.0087 0.9878
10.500 1.0081 0.02265 0.01765 0.0200 0.0085 0.9891
10.750 1.0289 0.02353 0.01866 0.0206 0.0083 0.9908
11.000 1.0462 0.02453 0.01981 0.0218 0.0081 0.9928
11.250 1.0608 0.02569 0.02113 0.0234 0.0078 0.9945
11.500 1.0778 0.02697 0.02258 0.0243 0.0076 0.9954
11.750 1.0920 0.02841 0.02422 0.0256 0.0074 0.9965
12.000 1.1042 0.02992 0.02591 0.0270 0.0072 0.9978
12.250 1.1149 0.03143 0.02759 0.0285 0.0071 0.9991
12.500 1.1206 0.03293 0.02925 0.0308 0.0069 1.0000
12.750 1.1103 0.03412 0.03056 0.0364 0.0069 1.0000
13.000 1.1012 0.03528 0.03182 0.0416 0.0068 1.0000
13.250 1.0890 0.03678 0.03345 0.0468 0.0068 1.0000
13.500 1.0773 0.03834 0.03513 0.0516 0.0067 1.0000
13.750 1.0650 0.04011 0.03701 0.0560 0.0066 1.0000
14.000 1.0485 0.04246 0.03951 0.0602 0.0066 1.0000
14.250 1.0296 0.04532 0.04253 0.0637 0.0066 1.0000
14.500 1.0115 0.04853 0.04587 0.0661 0.0065 1.0000
14.750 0.9856 0.05318 0.05071 0.0674 0.0065 1.0000
15.000 0.9485 0.06048 0.05824 0.0661 0.0066 1.0000
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Polar data table (+)
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