NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.12 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca632a015-il-1000000.txt Download as CSV file: xf-naca632a015-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)A-015
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.3655 0.14060 0.13894 -0.0203 1.0000 0.0134
-15.000 -0.3661 0.13754 0.13587 -0.0221 1.0000 0.0134
-14.250 -0.8795 0.05357 0.05078 -0.0563 1.0000 0.0087
-13.750 -0.8996 0.04632 0.04327 -0.0575 1.0000 0.0088
-13.500 -0.9170 0.04222 0.03898 -0.0571 1.0000 0.0089
-13.250 -0.9255 0.03932 0.03594 -0.0563 1.0000 0.0089
-13.000 -0.9400 0.03573 0.03207 -0.0545 1.0000 0.0089
-12.750 -0.9396 0.03399 0.03024 -0.0530 1.0000 0.0090
-12.500 -0.9432 0.03173 0.02778 -0.0508 1.0000 0.0090
-12.250 -0.9444 0.02970 0.02558 -0.0484 1.0000 0.0090
-12.000 -0.9389 0.02862 0.02443 -0.0462 1.0000 0.0092
-11.750 -0.9315 0.02790 0.02367 -0.0439 1.0000 0.0094
-11.500 -0.9277 0.02656 0.02220 -0.0411 1.0000 0.0095
-11.250 -0.9245 0.02491 0.02036 -0.0379 1.0000 0.0094
-11.000 -0.9185 0.02413 0.01951 -0.0347 1.0000 0.0096
-10.750 -0.9141 0.02322 0.01850 -0.0311 1.0000 0.0097
-10.500 -0.9110 0.02265 0.01787 -0.0269 1.0000 0.0100
-10.250 -0.9071 0.02175 0.01687 -0.0230 1.0000 0.0099
-10.000 -0.8867 0.02090 0.01594 -0.0223 0.9991 0.0102
-9.750 -0.8551 0.01967 0.01459 -0.0239 0.9961 0.0103
-9.500 -0.8245 0.01884 0.01366 -0.0251 0.9912 0.0105
-9.250 -0.7926 0.01817 0.01292 -0.0265 0.9855 0.0107
-9.000 -0.7640 0.01729 0.01196 -0.0272 0.9771 0.0108
-8.750 -0.7354 0.01575 0.01033 -0.0284 0.9684 0.0114
-8.500 -0.6972 0.01489 0.00942 -0.0313 0.9594 0.0116
-8.250 -0.6547 0.01418 0.00868 -0.0350 0.9478 0.0121
-8.000 -0.6122 0.01356 0.00799 -0.0386 0.9300 0.0126
-7.750 -0.5829 0.01308 0.00737 -0.0393 0.9036 0.0131
-7.500 -0.5629 0.01276 0.00692 -0.0378 0.8775 0.0134
-7.250 -0.5479 0.01231 0.00635 -0.0354 0.8553 0.0139
-7.000 -0.5300 0.01200 0.00596 -0.0335 0.8369 0.0144
-6.750 -0.5102 0.01176 0.00565 -0.0320 0.8214 0.0153
-6.500 -0.4899 0.01152 0.00533 -0.0305 0.8085 0.0159
-6.250 -0.4696 0.01122 0.00497 -0.0290 0.7974 0.0168
-6.000 -0.4480 0.01100 0.00472 -0.0278 0.7873 0.0181
-5.750 -0.4251 0.01081 0.00448 -0.0268 0.7776 0.0193
-5.500 -0.4029 0.01059 0.00423 -0.0258 0.7689 0.0210
-5.250 -0.3786 0.01046 0.00407 -0.0250 0.7602 0.0235
-5.000 -0.3547 0.01030 0.00391 -0.0242 0.7522 0.0270
-4.750 -0.3305 0.01014 0.00375 -0.0235 0.7443 0.0305
-4.500 -0.3057 0.01004 0.00360 -0.0229 0.7368 0.0334
-4.250 -0.2813 0.00986 0.00343 -0.0223 0.7289 0.0361
-4.000 -0.2562 0.00978 0.00329 -0.0217 0.7213 0.0381
-3.750 -0.2317 0.00957 0.00308 -0.0210 0.7141 0.0405
-3.500 -0.2069 0.00945 0.00293 -0.0204 0.7066 0.0429
-3.250 -0.1811 0.00934 0.00280 -0.0200 0.6994 0.0451
-3.000 -0.1565 0.00917 0.00262 -0.0193 0.6916 0.0486
-2.750 -0.1312 0.00905 0.00248 -0.0188 0.6846 0.0521
-2.500 -0.1060 0.00890 0.00234 -0.0182 0.6773 0.0592
-2.250 -0.0821 0.00869 0.00220 -0.0174 0.6702 0.0841
-2.000 -0.0805 0.00694 0.00165 -0.0130 0.6632 0.4204
-1.750 -0.0612 0.00654 0.00154 -0.0113 0.6551 0.5160
-1.500 -0.0371 0.00638 0.00148 -0.0105 0.6448 0.5546
-1.250 -0.0122 0.00631 0.00144 -0.0099 0.6329 0.5797
-0.750 0.0395 0.00624 0.00139 -0.0089 0.6127 0.6172
-0.500 0.0654 0.00624 0.00138 -0.0085 0.6044 0.6338
-0.250 0.0917 0.00620 0.00139 -0.0081 0.5963 0.6518
0.000 0.1179 0.00623 0.00139 -0.0077 0.5882 0.6666
0.250 0.1444 0.00620 0.00141 -0.0074 0.5803 0.6805
1.000 0.2240 0.00627 0.00145 -0.0064 0.5540 0.7094
1.250 0.2514 0.00630 0.00146 -0.0063 0.5455 0.7166
1.500 0.2778 0.00634 0.00149 -0.0060 0.5370 0.7235
1.750 0.3047 0.00637 0.00151 -0.0058 0.5275 0.7310
2.000 0.3313 0.00642 0.00155 -0.0055 0.5181 0.7379
2.250 0.3574 0.00647 0.00159 -0.0052 0.5078 0.7452
2.750 0.4102 0.00658 0.00168 -0.0046 0.4880 0.7597
3.000 0.4366 0.00664 0.00173 -0.0043 0.4764 0.7676
3.250 0.4623 0.00670 0.00179 -0.0039 0.4631 0.7756
3.500 0.4878 0.00679 0.00186 -0.0035 0.4472 0.7841
3.750 0.5126 0.00689 0.00194 -0.0029 0.4296 0.7926
4.000 0.5366 0.00705 0.00204 -0.0022 0.4086 0.8023
4.250 0.5593 0.00723 0.00216 -0.0013 0.3792 0.8129
4.500 0.5807 0.00751 0.00231 -0.0001 0.3446 0.8243
4.750 0.6017 0.00779 0.00249 0.0011 0.3137 0.8377
5.000 0.6235 0.00800 0.00267 0.0022 0.2901 0.8523
5.250 0.6453 0.00821 0.00285 0.0033 0.2705 0.8691
5.500 0.6677 0.00839 0.00303 0.0043 0.2546 0.8880
5.750 0.6921 0.00856 0.00323 0.0048 0.2425 0.9085
6.000 0.7207 0.00876 0.00344 0.0045 0.2321 0.9286
6.250 0.7549 0.00900 0.00368 0.0028 0.2222 0.9445
6.500 0.7912 0.00925 0.00392 0.0007 0.2126 0.9565
6.750 0.8299 0.00957 0.00420 -0.0021 0.2028 0.9632
7.000 0.8647 0.00979 0.00442 -0.0039 0.1963 0.9708
7.250 0.9009 0.01010 0.00470 -0.0060 0.1879 0.9749
7.500 0.9327 0.01032 0.00493 -0.0072 0.1821 0.9810
7.750 0.9649 0.01064 0.00520 -0.0085 0.1739 0.9852
8.000 0.9997 0.01087 0.00544 -0.0104 0.1675 0.9884
8.250 1.0318 0.01121 0.00573 -0.0118 0.1584 0.9924
8.500 1.0655 0.01148 0.00599 -0.0135 0.1505 0.9954
8.750 1.0998 0.01181 0.00630 -0.0154 0.1412 0.9980
9.000 1.1335 0.01220 0.00663 -0.0172 0.1299 0.9999
9.250 1.1450 0.01253 0.00690 -0.0144 0.1199 1.0000
9.500 1.1557 0.01286 0.00720 -0.0114 0.1103 1.0000
9.750 1.1658 0.01325 0.00755 -0.0083 0.1011 1.0000
10.000 1.1748 0.01368 0.00794 -0.0050 0.0921 1.0000
10.250 1.1799 0.01408 0.00830 -0.0010 0.0855 1.0000
10.500 1.1870 0.01445 0.00867 0.0026 0.0790 1.0000
10.750 1.1941 0.01495 0.00914 0.0060 0.0721 1.0000
11.000 1.2040 0.01545 0.00962 0.0087 0.0663 1.0000
11.250 1.2146 0.01599 0.01016 0.0112 0.0615 1.0000
11.500 1.2251 0.01659 0.01075 0.0135 0.0573 1.0000
11.750 1.2362 0.01722 0.01140 0.0155 0.0539 1.0000
12.000 1.2483 0.01786 0.01206 0.0173 0.0514 1.0000
12.250 1.2587 0.01864 0.01285 0.0192 0.0489 1.0000
12.500 1.2693 0.01946 0.01370 0.0208 0.0465 1.0000
12.750 1.2822 0.02020 0.01449 0.0221 0.0449 1.0000
13.000 1.2920 0.02118 0.01549 0.0235 0.0425 1.0000
13.250 1.2986 0.02244 0.01677 0.0250 0.0400 1.0000
13.500 1.3122 0.02327 0.01767 0.0259 0.0386 1.0000
13.750 1.3227 0.02435 0.01880 0.0268 0.0369 1.0000
14.000 1.3301 0.02572 0.02019 0.0278 0.0353 1.0000
14.250 1.3356 0.02729 0.02181 0.0288 0.0337 1.0000
14.500 1.3467 0.02846 0.02304 0.0294 0.0326 1.0000
14.750 1.3556 0.02984 0.02447 0.0299 0.0315 1.0000
15.000 1.3620 0.03147 0.02614 0.0305 0.0304 1.0000
15.250 1.3658 0.03336 0.02807 0.0310 0.0296 1.0000
15.500 1.3667 0.03559 0.03037 0.0315 0.0287 1.0000
15.750 1.3736 0.03731 0.03216 0.0317 0.0281 1.0000
16.000 1.3772 0.03938 0.03431 0.0319 0.0277 1.0000
16.250 1.3807 0.04154 0.03655 0.0319 0.0271 1.0000
16.500 1.3823 0.04396 0.03905 0.0318 0.0267 1.0000
16.750 1.3826 0.04657 0.04172 0.0316 0.0262 1.0000
17.000 1.3812 0.04945 0.04467 0.0312 0.0257 1.0000
17.250 1.3770 0.05277 0.04807 0.0307 0.0253 1.0000
17.500 1.3703 0.05644 0.05182 0.0299 0.0247 1.0000
17.750 1.3608 0.06058 0.05606 0.0289 0.0244 1.0000
18.000 1.3557 0.06430 0.05986 0.0278 0.0240 1.0000
18.250 1.3515 0.06794 0.06360 0.0268 0.0238 1.0000
18.500 1.3456 0.07187 0.06763 0.0255 0.0236 1.0000
18.750 1.3360 0.07640 0.07226 0.0240 0.0234 1.0000
19.000 1.3266 0.08099 0.07696 0.0223 0.0232 1.0000
19.250 1.3176 0.08558 0.08164 0.0206 0.0228 1.0000
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Polar data table (+)
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