NACA 23112 (naca23112-jf) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23112 (naca23112-jf) Reynolds number: 500,000 Max Cl/Cd: 77.87 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23112-jf-500000.txt Download as CSV file: xf-naca23112-jf-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6033 0.08733 0.08504 -0.0099 1.0000 0.0307
-10.000 -0.6295 0.07557 0.07325 -0.0219 1.0000 0.0307
-9.750 -0.7955 0.04577 0.04221 -0.0227 1.0000 0.0239
-9.500 -0.7971 0.04177 0.03799 -0.0206 1.0000 0.0237
-9.250 -0.8048 0.03607 0.03184 -0.0173 1.0000 0.0236
-9.000 -0.8093 0.03043 0.02553 -0.0135 1.0000 0.0238
-8.750 -0.8023 0.02691 0.02156 -0.0108 1.0000 0.0243
-8.500 -0.7833 0.02601 0.02066 -0.0096 1.0000 0.0248
-8.250 -0.7625 0.02570 0.02038 -0.0085 1.0000 0.0253
-8.000 -0.7441 0.02476 0.01936 -0.0069 1.0000 0.0259
-7.750 -0.7276 0.02308 0.01745 -0.0049 1.0000 0.0264
-7.500 -0.7101 0.02153 0.01568 -0.0030 1.0000 0.0270
-7.250 -0.6918 0.02023 0.01417 -0.0011 1.0000 0.0277
-7.000 -0.6729 0.01938 0.01314 0.0007 1.0000 0.0283
-6.750 -0.6545 0.01794 0.01162 0.0024 1.0000 0.0291
-6.500 -0.6356 0.01747 0.01117 0.0040 1.0000 0.0299
-6.250 -0.6167 0.01707 0.01075 0.0057 1.0000 0.0308
-6.000 -0.5882 0.01645 0.01009 0.0055 0.9986 0.0319
-5.750 -0.5502 0.01573 0.00926 0.0034 0.9957 0.0331
-5.500 -0.5138 0.01466 0.00816 0.0016 0.9927 0.0344
-5.250 -0.4766 0.01413 0.00767 -0.0005 0.9882 0.0360
-5.000 -0.4370 0.01369 0.00722 -0.0029 0.9845 0.0380
-4.750 -0.3982 0.01328 0.00677 -0.0050 0.9792 0.0395
-4.500 -0.3619 0.01236 0.00589 -0.0069 0.9711 0.0419
-4.250 -0.3284 0.01198 0.00552 -0.0078 0.9579 0.0443
-4.000 -0.2977 0.01172 0.00523 -0.0081 0.9431 0.0465
-3.750 -0.2721 0.01112 0.00463 -0.0075 0.9261 0.0495
-3.500 -0.2462 0.01086 0.00434 -0.0067 0.9066 0.0524
-3.250 -0.2206 0.01067 0.00408 -0.0058 0.8849 0.0553
-3.000 -0.1966 0.01031 0.00369 -0.0048 0.8611 0.0600
-2.750 -0.1711 0.01017 0.00346 -0.0039 0.8356 0.0642
-2.500 -0.1463 0.00992 0.00314 -0.0031 0.8092 0.0707
-2.250 -0.1203 0.00982 0.00294 -0.0024 0.7830 0.0777
-2.000 -0.0948 0.00964 0.00270 -0.0017 0.7561 0.0897
-1.750 -0.0696 0.00939 0.00247 -0.0010 0.7278 0.1189
-1.500 -0.0567 0.00762 0.00206 0.0011 0.7027 0.5041
-1.250 -0.0369 0.00706 0.00199 0.0029 0.6771 0.6517
-1.000 -0.0144 0.00683 0.00198 0.0043 0.6518 0.7365
-0.750 0.0094 0.00676 0.00200 0.0056 0.6249 0.7957
-0.500 0.0343 0.00678 0.00204 0.0067 0.5979 0.8364
-0.250 0.0596 0.00687 0.00209 0.0077 0.5714 0.8682
0.000 0.0853 0.00700 0.00216 0.0086 0.5456 0.8935
0.250 0.1116 0.00717 0.00224 0.0093 0.5195 0.9125
0.500 0.1384 0.00738 0.00234 0.0100 0.4920 0.9297
0.750 0.1661 0.00761 0.00246 0.0105 0.4651 0.9440
1.000 0.1960 0.00790 0.00261 0.0105 0.4388 0.9574
1.250 0.2328 0.00817 0.00274 0.0087 0.4107 0.9629
1.500 0.2635 0.00839 0.00282 0.0082 0.3853 0.9698
1.750 0.3022 0.00864 0.00292 0.0059 0.3597 0.9721
2.000 0.3410 0.00886 0.00301 0.0035 0.3386 0.9745
2.250 0.3782 0.00907 0.00311 0.0015 0.3205 0.9778
2.500 0.4109 0.00929 0.00323 0.0004 0.3059 0.9829
2.750 0.4498 0.00949 0.00333 -0.0021 0.2929 0.9848
3.000 0.4880 0.00963 0.00343 -0.0043 0.2824 0.9873
3.250 0.5247 0.00981 0.00354 -0.0063 0.2730 0.9904
3.500 0.5599 0.01000 0.00367 -0.0080 0.2645 0.9938
3.750 0.5979 0.01014 0.00378 -0.0103 0.2573 0.9957
4.000 0.6351 0.01029 0.00389 -0.0124 0.2500 0.9981
4.250 0.6698 0.01048 0.00404 -0.0141 0.2434 1.0000
4.500 0.6936 0.01057 0.00414 -0.0134 0.2385 1.0000
4.750 0.7168 0.01073 0.00427 -0.0126 0.2333 1.0000
5.000 0.7396 0.01093 0.00444 -0.0118 0.2282 1.0000
5.250 0.7631 0.01103 0.00458 -0.0110 0.2238 1.0000
5.500 0.7860 0.01119 0.00473 -0.0101 0.2192 1.0000
5.750 0.8079 0.01149 0.00496 -0.0091 0.2139 1.0000
6.000 0.8313 0.01158 0.00512 -0.0083 0.2102 1.0000
6.250 0.8542 0.01173 0.00529 -0.0074 0.2057 1.0000
6.500 0.8762 0.01198 0.00550 -0.0064 0.2009 1.0000
6.750 0.8986 0.01220 0.00575 -0.0054 0.1967 1.0000
7.000 0.9217 0.01234 0.00593 -0.0045 0.1924 1.0000
7.250 0.9440 0.01255 0.00613 -0.0035 0.1877 1.0000
7.500 0.9657 0.01285 0.00642 -0.0025 0.1830 1.0000
7.750 0.9891 0.01299 0.00662 -0.0017 0.1786 1.0000
8.000 1.0116 0.01320 0.00684 -0.0008 0.1737 1.0000
8.250 1.0333 0.01352 0.00714 0.0002 0.1686 1.0000
8.500 1.0568 0.01367 0.00737 0.0010 0.1638 1.0000
8.750 1.0790 0.01394 0.00762 0.0019 0.1584 1.0000
9.000 1.1014 0.01422 0.00793 0.0027 0.1532 1.0000
9.250 1.1244 0.01444 0.00820 0.0035 0.1477 1.0000
9.500 1.1456 0.01483 0.00855 0.0044 0.1418 1.0000
9.750 1.1693 0.01505 0.00884 0.0050 0.1364 1.0000
10.000 1.1908 0.01545 0.00922 0.0059 0.1300 1.0000
10.250 1.2138 0.01574 0.00958 0.0065 0.1242 1.0000
10.500 1.2350 0.01619 0.01000 0.0073 0.1174 1.0000
10.750 1.2573 0.01655 0.01042 0.0080 0.1112 1.0000
11.000 1.2773 0.01710 0.01094 0.0089 0.1040 1.0000
11.250 1.2987 0.01754 0.01142 0.0097 0.0971 1.0000
11.500 1.3182 0.01812 0.01201 0.0106 0.0901 1.0000
11.750 1.3362 0.01880 0.01268 0.0117 0.0826 1.0000
12.000 1.3546 0.01942 0.01333 0.0127 0.0759 1.0000
12.250 1.3707 0.02020 0.01412 0.0140 0.0693 1.0000
12.500 1.3844 0.02110 0.01501 0.0155 0.0629 1.0000
12.750 1.3983 0.02190 0.01586 0.0170 0.0578 1.0000
13.000 1.4053 0.02297 0.01695 0.0194 0.0532 1.0000
13.250 1.4148 0.02392 0.01797 0.0213 0.0494 1.0000
13.500 1.4176 0.02538 0.01945 0.0235 0.0459 1.0000
13.750 1.4262 0.02655 0.02072 0.0248 0.0432 1.0000
14.000 1.4287 0.02828 0.02251 0.0262 0.0407 1.0000
14.250 1.4287 0.03040 0.02471 0.0271 0.0386 1.0000
14.500 1.4323 0.03241 0.02684 0.0275 0.0368 1.0000
14.750 1.4309 0.03514 0.02966 0.0274 0.0352 1.0000
15.000 1.4234 0.03884 0.03346 0.0264 0.0340 1.0000
15.250 1.4136 0.04318 0.03792 0.0248 0.0330 1.0000
15.500 1.4084 0.04717 0.04207 0.0232 0.0321 1.0000
15.750 1.3984 0.05197 0.04701 0.0210 0.0313 1.0000
16.000 1.3840 0.05750 0.05267 0.0185 0.0307 1.0000
16.250 1.3657 0.06365 0.05896 0.0157 0.0303 1.0000
16.500 1.3445 0.07024 0.06568 0.0127 0.0299 1.0000
16.750 1.3221 0.07705 0.07261 0.0097 0.0297 1.0000
17.000 1.2998 0.08395 0.07962 0.0067 0.0294 1.0000
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