NACA 23112 (naca23112-jf) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23112 (naca23112-jf) Reynolds number: 200,000 Max Cl/Cd: 55.47 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23112-jf-200000-n5.txt Download as CSV file: xf-naca23112-jf-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23112
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6439 0.08186 0.07812 -0.0169 1.0000 0.0231
-10.500 -0.6759 0.07127 0.06741 -0.0259 1.0000 0.0228
-10.250 -0.7054 0.06476 0.06073 -0.0284 1.0000 0.0227
-10.000 -0.7315 0.05973 0.05551 -0.0271 1.0000 0.0227
-9.750 -0.7514 0.05419 0.04969 -0.0253 1.0000 0.0228
-9.500 -0.7671 0.04814 0.04323 -0.0229 1.0000 0.0230
-9.250 -0.7822 0.04107 0.03555 -0.0195 1.0000 0.0234
-9.000 -0.7913 0.03433 0.02792 -0.0156 1.0000 0.0241
-8.750 -0.7744 0.03322 0.02674 -0.0144 1.0000 0.0244
-8.500 -0.7564 0.03230 0.02576 -0.0132 1.0000 0.0249
-8.250 -0.7384 0.03128 0.02464 -0.0119 1.0000 0.0256
-8.000 -0.7218 0.02971 0.02284 -0.0103 1.0000 0.0264
-7.750 -0.7058 0.02754 0.02032 -0.0084 1.0000 0.0274
-7.500 -0.6884 0.02540 0.01778 -0.0066 1.0000 0.0282
-7.250 -0.6690 0.02413 0.01637 -0.0051 1.0000 0.0288
-7.000 -0.6491 0.02333 0.01553 -0.0038 1.0000 0.0294
-6.750 -0.6289 0.02264 0.01480 -0.0024 1.0000 0.0303
-6.500 -0.6088 0.02188 0.01395 -0.0010 1.0000 0.0315
-6.250 -0.5885 0.02097 0.01288 0.0005 1.0000 0.0329
-6.000 -0.5685 0.02007 0.01187 0.0020 1.0000 0.0338
-5.750 -0.5491 0.01942 0.01125 0.0035 1.0000 0.0347
-5.500 -0.5165 0.01874 0.01056 0.0023 0.9958 0.0360
-5.250 -0.4802 0.01806 0.00981 0.0005 0.9897 0.0382
-5.000 -0.4434 0.01730 0.00901 -0.0015 0.9836 0.0403
-4.750 -0.4089 0.01669 0.00844 -0.0030 0.9749 0.0421
-4.500 -0.3746 0.01611 0.00785 -0.0043 0.9650 0.0446
-4.250 -0.3402 0.01553 0.00725 -0.0056 0.9540 0.0475
-4.000 -0.3071 0.01503 0.00678 -0.0067 0.9405 0.0504
-3.750 -0.2751 0.01457 0.00628 -0.0074 0.9236 0.0537
-3.500 -0.2457 0.01410 0.00581 -0.0075 0.9007 0.0576
-3.250 -0.2166 0.01374 0.00539 -0.0073 0.8743 0.0621
-3.000 -0.1904 0.01341 0.00498 -0.0067 0.8456 0.0669
-2.750 -0.1648 0.01314 0.00465 -0.0059 0.8181 0.0734
-2.500 -0.1396 0.01290 0.00432 -0.0050 0.7907 0.0810
-2.250 -0.1144 0.01270 0.00403 -0.0041 0.7630 0.0922
-2.000 -0.0896 0.01246 0.00376 -0.0033 0.7358 0.1121
-1.750 -0.0739 0.01106 0.00333 -0.0015 0.7103 0.3730
-1.500 -0.0567 0.01025 0.00319 0.0007 0.6850 0.5573
-1.250 -0.0365 0.00988 0.00317 0.0027 0.6587 0.6683
-1.000 -0.0134 0.00975 0.00321 0.0043 0.6324 0.7443
-0.750 0.0117 0.00977 0.00327 0.0056 0.6066 0.7994
-0.500 0.0385 0.00988 0.00335 0.0065 0.5799 0.8422
-0.250 0.0669 0.01007 0.00345 0.0071 0.5527 0.8742
0.000 0.0981 0.01033 0.00359 0.0071 0.5254 0.9018
0.250 0.1290 0.01058 0.00370 0.0070 0.4995 0.9225
0.500 0.1619 0.01080 0.00374 0.0062 0.4726 0.9320
0.750 0.1914 0.01099 0.00377 0.0059 0.4470 0.9417
1.000 0.2261 0.01121 0.00382 0.0046 0.4224 0.9476
1.250 0.2562 0.01140 0.00388 0.0042 0.4005 0.9563
1.500 0.2928 0.01162 0.00394 0.0023 0.3777 0.9607
2.000 0.3610 0.01203 0.00410 -0.0004 0.3412 0.9721
2.500 0.4306 0.01243 0.00430 -0.0036 0.3118 0.9821
2.750 0.4667 0.01261 0.00440 -0.0055 0.2996 0.9859
3.000 0.5021 0.01281 0.00453 -0.0072 0.2896 0.9901
3.250 0.5366 0.01301 0.00466 -0.0088 0.2798 0.9943
3.500 0.5724 0.01319 0.00480 -0.0107 0.2711 0.9977
3.750 0.6032 0.01339 0.00496 -0.0115 0.2636 1.0000
4.000 0.6259 0.01358 0.00512 -0.0107 0.2578 1.0000
4.250 0.6487 0.01376 0.00529 -0.0098 0.2515 1.0000
4.500 0.6710 0.01400 0.00548 -0.0089 0.2459 1.0000
4.750 0.6938 0.01420 0.00569 -0.0080 0.2408 1.0000
5.000 0.7163 0.01441 0.00591 -0.0071 0.2355 1.0000
5.250 0.7383 0.01469 0.00615 -0.0061 0.2305 1.0000
5.500 0.7609 0.01492 0.00640 -0.0052 0.2257 1.0000
5.750 0.7834 0.01516 0.00667 -0.0043 0.2208 1.0000
6.000 0.8054 0.01544 0.00695 -0.0033 0.2162 1.0000
6.250 0.8276 0.01573 0.00725 -0.0024 0.2117 1.0000
6.500 0.8503 0.01599 0.00756 -0.0015 0.2069 1.0000
6.750 0.8724 0.01628 0.00786 -0.0005 0.2023 1.0000
7.000 0.8941 0.01663 0.00820 0.0005 0.1980 1.0000
7.250 0.9168 0.01690 0.00856 0.0014 0.1932 1.0000
7.500 0.9389 0.01720 0.00890 0.0023 0.1884 1.0000
7.750 0.9601 0.01758 0.00926 0.0033 0.1841 1.0000
8.000 0.9827 0.01787 0.00967 0.0041 0.1792 1.0000
8.250 1.0048 0.01820 0.01005 0.0050 0.1741 1.0000
8.500 1.0258 0.01860 0.01043 0.0060 0.1695 1.0000
8.750 1.0484 0.01892 0.01089 0.0068 0.1641 1.0000
9.000 1.0700 0.01929 0.01130 0.0076 0.1587 1.0000
9.250 1.0912 0.01971 0.01176 0.0085 0.1535 1.0000
9.500 1.1129 0.02009 0.01225 0.0093 0.1474 1.0000
9.750 1.1329 0.02056 0.01271 0.0103 0.1420 1.0000
10.000 1.1544 0.02098 0.01327 0.0110 0.1356 1.0000
10.250 1.1737 0.02150 0.01381 0.0120 0.1296 1.0000
10.500 1.1941 0.02200 0.01442 0.0129 0.1232 1.0000
10.750 1.2120 0.02261 0.01504 0.0140 0.1170 1.0000
11.000 1.2310 0.02319 0.01573 0.0150 0.1105 1.0000
11.250 1.2467 0.02392 0.01648 0.0162 0.1042 1.0000
11.500 1.2637 0.02461 0.01728 0.0174 0.0977 1.0000
11.750 1.2771 0.02546 0.01817 0.0188 0.0917 1.0000
12.000 1.2900 0.02631 0.01910 0.0203 0.0855 1.0000
12.250 1.2981 0.02732 0.02017 0.0224 0.0804 1.0000
12.500 1.3064 0.02840 0.02133 0.0242 0.0750 1.0000
12.750 1.3115 0.02975 0.02274 0.0259 0.0706 1.0000
13.000 1.3173 0.03118 0.02428 0.0272 0.0661 1.0000
13.250 1.3184 0.03310 0.02625 0.0284 0.0624 1.0000
13.500 1.3216 0.03502 0.02831 0.0290 0.0589 1.0000
13.750 1.3208 0.03750 0.03090 0.0292 0.0557 1.0000
14.000 1.3162 0.04063 0.03411 0.0287 0.0534 1.0000
14.250 1.3139 0.04378 0.03743 0.0279 0.0510 1.0000
14.500 1.3072 0.04769 0.04148 0.0264 0.0490 1.0000
14.750 1.2962 0.05243 0.04634 0.0243 0.0474 1.0000
15.000 1.2812 0.05795 0.05198 0.0216 0.0463 1.0000
15.250 1.2663 0.06359 0.05777 0.0189 0.0453 1.0000
15.500 1.2504 0.06948 0.06383 0.0161 0.0443 1.0000
15.750 1.2320 0.07581 0.07030 0.0131 0.0435 1.0000
16.000 1.2122 0.08245 0.07707 0.0100 0.0427 1.0000
16.250 1.1926 0.08922 0.08396 0.0068 0.0419 1.0000
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