NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 200,000 Max Cl/Cd: 47.85 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca641112-il-200000-n5.txt Download as CSV file: xf-naca641112-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-112
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7259 0.08171 0.07796 -0.0243 1.0000 0.0187
-12.000 -0.7616 0.07108 0.06717 -0.0319 1.0000 0.0185
-11.750 -0.7885 0.06394 0.05985 -0.0363 1.0000 0.0183
-11.500 -0.8128 0.05817 0.05390 -0.0389 1.0000 0.0182
-11.250 -0.8338 0.05348 0.04899 -0.0398 1.0000 0.0182
-11.000 -0.8526 0.04949 0.04476 -0.0393 1.0000 0.0184
-10.750 -0.8677 0.04614 0.04115 -0.0376 1.0000 0.0184
-10.500 -0.8779 0.04306 0.03778 -0.0352 1.0000 0.0186
-10.250 -0.8803 0.03990 0.03425 -0.0334 1.0000 0.0189
-10.000 -0.8771 0.03698 0.03095 -0.0317 1.0000 0.0193
-9.750 -0.8686 0.03445 0.02804 -0.0303 1.0000 0.0197
-9.500 -0.8565 0.03245 0.02568 -0.0290 1.0000 0.0203
-9.250 -0.8406 0.03059 0.02372 -0.0282 1.0000 0.0209
-9.000 -0.8227 0.02930 0.02233 -0.0275 1.0000 0.0215
-8.750 -0.8040 0.02795 0.02084 -0.0268 1.0000 0.0221
-8.500 -0.7845 0.02656 0.01928 -0.0260 1.0000 0.0227
-8.250 -0.7643 0.02524 0.01780 -0.0252 1.0000 0.0233
-8.000 -0.7440 0.02402 0.01645 -0.0244 1.0000 0.0240
-7.750 -0.7239 0.02292 0.01523 -0.0234 1.0000 0.0247
-7.500 -0.7047 0.02202 0.01423 -0.0223 1.0000 0.0256
-7.250 -0.6795 0.02090 0.01302 -0.0225 0.9917 0.0268
-7.000 -0.6482 0.01983 0.01195 -0.0241 0.9785 0.0283
-6.750 -0.6165 0.01890 0.01098 -0.0255 0.9666 0.0298
-6.500 -0.5858 0.01806 0.01006 -0.0267 0.9549 0.0314
-6.250 -0.5565 0.01732 0.00921 -0.0275 0.9430 0.0332
-6.000 -0.5301 0.01653 0.00837 -0.0277 0.9305 0.0355
-5.500 -0.4798 0.01549 0.00718 -0.0274 0.9062 0.0427
-5.250 -0.4562 0.01493 0.00659 -0.0268 0.8945 0.0473
-5.000 -0.4320 0.01452 0.00611 -0.0263 0.8838 0.0542
-4.750 -0.4085 0.01403 0.00563 -0.0256 0.8735 0.0658
-4.500 -0.3854 0.01347 0.00516 -0.0250 0.8628 0.0924
-4.250 -0.3637 0.01268 0.00468 -0.0244 0.8530 0.1613
-4.000 -0.3442 0.01160 0.00414 -0.0237 0.8436 0.2906
-3.750 -0.3245 0.01067 0.00391 -0.0228 0.8337 0.4535
-3.500 -0.2994 0.01048 0.00380 -0.0222 0.8253 0.5096
-3.250 -0.2735 0.01036 0.00373 -0.0217 0.8163 0.5453
-3.000 -0.2477 0.01030 0.00372 -0.0211 0.8082 0.5854
-2.750 -0.2224 0.01031 0.00381 -0.0203 0.7998 0.6237
-2.500 -0.1958 0.01033 0.00380 -0.0198 0.7916 0.6463
-2.250 -0.1687 0.01029 0.00372 -0.0196 0.7836 0.6548
-2.000 -0.1409 0.01026 0.00362 -0.0195 0.7756 0.6633
-1.750 -0.1134 0.01024 0.00354 -0.0193 0.7683 0.6709
-1.500 -0.0854 0.01021 0.00345 -0.0194 0.7606 0.6778
-1.250 -0.0578 0.01018 0.00339 -0.0192 0.7532 0.6838
-1.000 -0.0297 0.01016 0.00331 -0.0193 0.7455 0.6911
-0.750 -0.0020 0.01014 0.00327 -0.0192 0.7383 0.6968
-0.500 0.0260 0.01014 0.00324 -0.0192 0.7312 0.7035
-0.250 0.0539 0.01013 0.00322 -0.0192 0.7243 0.7102
0.000 0.0816 0.01014 0.00322 -0.0191 0.7180 0.7173
0.250 0.1096 0.01015 0.00323 -0.0191 0.7107 0.7246
0.500 0.1373 0.01017 0.00325 -0.0190 0.7046 0.7313
0.750 0.1654 0.01019 0.00329 -0.0191 0.6974 0.7389
1.000 0.1929 0.01021 0.00334 -0.0189 0.6916 0.7458
1.250 0.2210 0.01025 0.00341 -0.0190 0.6853 0.7542
1.500 0.2484 0.01029 0.00350 -0.0188 0.6788 0.7615
1.750 0.2762 0.01034 0.00357 -0.0188 0.6731 0.7699
2.000 0.3036 0.01038 0.00371 -0.0187 0.6661 0.7772
2.250 0.3311 0.01044 0.00377 -0.0185 0.6591 0.7856
2.500 0.3582 0.01047 0.00391 -0.0183 0.6502 0.7938
2.750 0.3854 0.01054 0.00402 -0.0181 0.6434 0.8025
3.000 0.4118 0.01057 0.00410 -0.0176 0.6299 0.8114
3.250 0.4370 0.01055 0.00408 -0.0168 0.6026 0.8199
3.500 0.4617 0.01061 0.00406 -0.0160 0.5676 0.8296
3.750 0.4859 0.01070 0.00413 -0.0151 0.5315 0.8386
4.000 0.5104 0.01085 0.00423 -0.0144 0.4956 0.8484
4.250 0.5330 0.01114 0.00436 -0.0133 0.4327 0.8590
4.500 0.5491 0.01203 0.00470 -0.0116 0.3035 0.8701
4.750 0.5644 0.01318 0.00530 -0.0100 0.1844 0.8823
5.000 0.5819 0.01410 0.00586 -0.0087 0.1083 0.8954
5.250 0.6020 0.01476 0.00637 -0.0075 0.0732 0.9096
5.500 0.6235 0.01533 0.00689 -0.0066 0.0571 0.9249
5.750 0.6479 0.01582 0.00741 -0.0063 0.0485 0.9418
6.000 0.6759 0.01640 0.00804 -0.0068 0.0425 0.9602
6.500 0.7300 0.01785 0.00957 -0.0080 0.0351 1.0000
6.750 0.7516 0.01852 0.01031 -0.0074 0.0330 1.0000
7.000 0.7729 0.01922 0.01104 -0.0068 0.0307 1.0000
7.250 0.7933 0.02000 0.01182 -0.0061 0.0288 1.0000
7.500 0.8116 0.02108 0.01292 -0.0052 0.0272 1.0000
7.750 0.8324 0.02195 0.01387 -0.0044 0.0263 1.0000
8.000 0.8529 0.02292 0.01492 -0.0036 0.0253 1.0000
8.250 0.8735 0.02396 0.01604 -0.0029 0.0245 1.0000
8.500 0.8942 0.02505 0.01722 -0.0022 0.0236 1.0000
8.750 0.9148 0.02620 0.01844 -0.0016 0.0230 1.0000
9.000 0.9351 0.02741 0.01972 -0.0010 0.0223 1.0000
9.250 0.9545 0.02871 0.02107 -0.0004 0.0216 1.0000
9.500 0.9736 0.03042 0.02291 0.0003 0.0209 1.0000
9.750 0.9913 0.03186 0.02459 0.0012 0.0203 1.0000
10.000 1.0074 0.03363 0.02664 0.0022 0.0198 1.0000
10.250 1.0211 0.03563 0.02890 0.0034 0.0194 1.0000
10.500 1.0315 0.03779 0.03133 0.0048 0.0190 1.0000
10.750 1.0373 0.04002 0.03384 0.0066 0.0187 1.0000
11.000 1.0382 0.04238 0.03646 0.0088 0.0184 1.0000
11.250 1.0359 0.04483 0.03916 0.0109 0.0182 1.0000
11.500 1.0320 0.04732 0.04186 0.0126 0.0179 1.0000
11.750 1.0259 0.05005 0.04480 0.0138 0.0177 1.0000
12.000 1.0192 0.05289 0.04783 0.0145 0.0175 1.0000
12.250 1.0110 0.05600 0.05111 0.0147 0.0173 1.0000
12.500 0.9977 0.06000 0.05531 0.0143 0.0171 1.0000
12.750 0.9941 0.06281 0.05820 0.0135 0.0168 1.0000
13.000 0.9751 0.06819 0.06380 0.0116 0.0168 1.0000
13.250 0.9470 0.07555 0.07142 0.0079 0.0169 1.0000
13.500 0.9175 0.08414 0.08024 0.0027 0.0169 1.0000
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