NACA 23112 (naca23112-jf) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23112 (naca23112-jf) Reynolds number: 200,000 Max Cl/Cd: 50.6 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23112-jf-200000.txt Download as CSV file: xf-naca23112-jf-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5734 0.08913 0.08557 -0.0113 1.0000 0.0611
-9.500 -0.5920 0.08070 0.07714 -0.0201 1.0000 0.0618
-9.250 -0.6164 0.07489 0.07124 -0.0238 1.0000 0.0625
-9.000 -0.6513 0.07076 0.06680 -0.0240 1.0000 0.0642
-8.750 -0.5963 0.05541 0.05164 -0.0283 1.0000 0.0667
-8.500 -0.5894 0.05210 0.04835 -0.0273 1.0000 0.0678
-8.250 -0.5879 0.04875 0.04495 -0.0260 1.0000 0.0691
-8.000 -0.5880 0.04535 0.04145 -0.0244 1.0000 0.0708
-7.750 -0.5898 0.04207 0.03797 -0.0222 1.0000 0.0736
-7.500 -0.6019 0.04247 0.03762 -0.0162 1.0000 0.0769
-7.250 -0.5978 0.03464 0.02998 -0.0162 1.0000 0.0789
-7.000 -0.5870 0.03195 0.02732 -0.0146 1.0000 0.0805
-6.750 -0.5781 0.02968 0.02499 -0.0124 1.0000 0.0828
-6.500 -0.5735 0.03175 0.02648 -0.0070 1.0000 0.0903
-6.000 -0.5738 0.02967 0.02260 0.0006 1.0000 0.0543
-5.750 -0.5572 0.02734 0.02007 0.0026 1.0000 0.0539
-5.500 -0.5400 0.02603 0.01847 0.0049 1.0000 0.0546
-5.250 -0.5222 0.02397 0.01622 0.0067 1.0000 0.0558
-5.000 -0.5029 0.02251 0.01471 0.0081 1.0000 0.0569
-4.750 -0.4832 0.02145 0.01361 0.0095 1.0000 0.0581
-4.500 -0.4635 0.02056 0.01268 0.0110 1.0000 0.0595
-4.250 -0.4381 0.01986 0.01189 0.0113 0.9988 0.0622
-4.000 -0.3914 0.01908 0.01095 0.0078 0.9932 0.0652
-3.750 -0.3486 0.01748 0.00947 0.0047 0.9869 0.0691
-3.500 -0.3019 0.01676 0.00875 0.0010 0.9791 0.0747
-3.250 -0.2549 0.01558 0.00764 -0.0027 0.9712 0.0802
-3.000 -0.2109 0.01487 0.00698 -0.0058 0.9602 0.0884
-2.750 -0.1733 0.01397 0.00617 -0.0076 0.9478 0.0973
-2.500 -0.1386 0.01328 0.00552 -0.0087 0.9329 0.1103
-2.250 -0.1077 0.01261 0.00493 -0.0090 0.9152 0.1333
-2.000 -0.0997 0.01006 0.00436 -0.0055 0.8949 0.5747
-1.750 -0.0826 0.00939 0.00449 -0.0015 0.8747 0.7754
-1.500 -0.0583 0.00941 0.00462 0.0009 0.8511 0.8429
-1.250 -0.0305 0.00960 0.00476 0.0026 0.8265 0.8813
-1.000 -0.0033 0.00983 0.00487 0.0041 0.7999 0.9091
-0.750 0.0319 0.01018 0.00504 0.0040 0.7722 0.9282
-0.500 0.0718 0.01054 0.00520 0.0027 0.7411 0.9438
-0.250 0.1225 0.01095 0.00537 -0.0009 0.7064 0.9581
0.000 0.1716 0.01126 0.00545 -0.0046 0.6698 0.9711
0.250 0.2153 0.01138 0.00534 -0.0077 0.6319 0.9778
0.500 0.2550 0.01150 0.00522 -0.0102 0.5943 0.9850
0.750 0.2968 0.01161 0.00509 -0.0132 0.5563 0.9912
1.000 0.3389 0.01171 0.00496 -0.0163 0.5167 0.9968
1.250 0.3737 0.01183 0.00485 -0.0181 0.4808 1.0000
1.500 0.3970 0.01196 0.00479 -0.0175 0.4521 1.0000
1.750 0.4204 0.01211 0.00476 -0.0170 0.4265 1.0000
2.000 0.4438 0.01228 0.00477 -0.0165 0.4044 1.0000
2.250 0.4674 0.01245 0.00481 -0.0159 0.3850 1.0000
2.500 0.4910 0.01264 0.00488 -0.0154 0.3689 1.0000
2.750 0.5146 0.01286 0.00498 -0.0148 0.3555 1.0000
3.000 0.5380 0.01307 0.00509 -0.0141 0.3432 1.0000
3.250 0.5612 0.01326 0.00525 -0.0134 0.3320 1.0000
3.500 0.5842 0.01354 0.00543 -0.0127 0.3229 1.0000
3.750 0.6073 0.01375 0.00562 -0.0119 0.3139 1.0000
4.000 0.6302 0.01405 0.00584 -0.0111 0.3060 1.0000
4.250 0.6531 0.01428 0.00606 -0.0102 0.2980 1.0000
4.500 0.6760 0.01464 0.00635 -0.0094 0.2914 1.0000
4.750 0.6988 0.01488 0.00662 -0.0085 0.2844 1.0000
5.000 0.7215 0.01525 0.00689 -0.0077 0.2781 1.0000
5.250 0.7442 0.01554 0.00726 -0.0068 0.2717 1.0000
5.500 0.7669 0.01585 0.00756 -0.0059 0.2657 1.0000
5.750 0.7896 0.01632 0.00795 -0.0051 0.2602 1.0000
6.000 0.8120 0.01659 0.00833 -0.0041 0.2541 1.0000
6.250 0.8347 0.01694 0.00866 -0.0032 0.2486 1.0000
6.500 0.8574 0.01744 0.00914 -0.0024 0.2434 1.0000
6.750 0.8796 0.01774 0.00955 -0.0014 0.2376 1.0000
7.000 0.9022 0.01812 0.00991 -0.0005 0.2323 1.0000
7.250 0.9247 0.01865 0.01045 0.0003 0.2272 1.0000
7.500 0.9466 0.01898 0.01089 0.0013 0.2214 1.0000
7.750 0.9692 0.01937 0.01126 0.0021 0.2163 1.0000
8.000 0.9910 0.01990 0.01186 0.0030 0.2110 1.0000
8.250 1.0126 0.02023 0.01229 0.0040 0.2052 1.0000
8.500 1.0351 0.02065 0.01266 0.0048 0.2001 1.0000
8.750 1.0561 0.02111 0.01328 0.0058 0.1944 1.0000
9.000 1.0776 0.02141 0.01364 0.0067 0.1886 1.0000
9.250 1.0997 0.02195 0.01412 0.0074 0.1832 1.0000
9.500 1.1195 0.02224 0.01463 0.0086 0.1769 1.0000
9.750 1.1408 0.02255 0.01491 0.0095 0.1713 1.0000
10.000 1.1604 0.02304 0.01554 0.0105 0.1651 1.0000
10.250 1.1804 0.02333 0.01589 0.0115 0.1589 1.0000
10.500 1.1994 0.02386 0.01648 0.0126 0.1528 1.0000
10.750 1.2178 0.02420 0.01694 0.0138 0.1461 1.0000
11.000 1.2355 0.02478 0.01754 0.0149 0.1399 1.0000
11.250 1.2520 0.02522 0.01812 0.0163 0.1330 1.0000
11.500 1.2672 0.02590 0.01884 0.0176 0.1266 1.0000
11.750 1.2813 0.02648 0.01952 0.0191 0.1196 1.0000
12.000 1.2931 0.02734 0.02045 0.0208 0.1131 1.0000
12.250 1.3022 0.02812 0.02130 0.0229 0.1067 1.0000
12.500 1.3080 0.02921 0.02247 0.0251 0.1007 1.0000
12.750 1.3128 0.03035 0.02367 0.0271 0.0950 1.0000
13.000 1.3158 0.03189 0.02529 0.0289 0.0897 1.0000
13.250 1.3183 0.03351 0.02700 0.0301 0.0846 1.0000
13.500 1.3177 0.03564 0.02916 0.0312 0.0803 1.0000
13.750 1.3180 0.03787 0.03155 0.0316 0.0760 1.0000
14.000 1.3151 0.04055 0.03423 0.0317 0.0726 1.0000
14.250 1.3117 0.04359 0.03742 0.0314 0.0693 1.0000
14.500 1.3078 0.04686 0.04083 0.0305 0.0663 1.0000
14.750 1.3025 0.05038 0.04440 0.0294 0.0638 1.0000
15.000 1.2960 0.05409 0.04814 0.0286 0.0615 1.0000
15.250 1.2876 0.05841 0.05267 0.0268 0.0595 1.0000
15.500 1.2793 0.06276 0.05714 0.0250 0.0576 1.0000
15.750 1.2716 0.06702 0.06146 0.0232 0.0558 1.0000
16.000 1.2690 0.07007 0.06440 0.0229 0.0537 1.0000
16.250 1.2552 0.07561 0.07018 0.0202 0.0527 1.0000
16.500 1.2417 0.08121 0.07597 0.0174 0.0515 1.0000
16.750 1.2294 0.08670 0.08160 0.0147 0.0502 1.0000
17.000 1.2198 0.09181 0.08681 0.0123 0.0490 1.0000
17.250 1.2153 0.09597 0.09100 0.0105 0.0476 1.0000
17.500 1.2178 0.09840 0.09336 0.0105 0.0459 1.0000
17.750 1.1992 0.10553 0.10069 0.0065 0.0454 1.0000
18.000 1.1791 0.11313 0.10849 0.0022 0.0449 1.0000
18.250 1.1564 0.12140 0.11696 -0.0026 0.0444 1.0000
18.500 1.1282 0.13112 0.12688 -0.0083 0.0442 1.0000
18.750 1.0791 0.14597 0.14198 -0.0172 0.0446 1.0000
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