NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M23 AIRFOIL (m23-il) Reynolds number: 200,000 Max Cl/Cd: 75.99 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m23-il-200000-n5.txt Download as CSV file: xf-m23-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M23 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3818 0.11191 0.10804 0.0158 0.6743 0.0190
-8.000 -0.3776 0.10908 0.10519 0.0126 0.6700 0.0191
-7.750 -0.3736 0.10618 0.10228 0.0096 0.6651 0.0191
-7.500 -0.3645 0.10270 0.09877 0.0065 0.6602 0.0192
-7.250 -0.3538 0.09912 0.09514 0.0035 0.6561 0.0192
-7.000 -0.3415 0.09543 0.09140 0.0004 0.6517 0.0192
-6.750 -0.3279 0.09150 0.08745 -0.0024 0.6468 0.0192
-6.500 -0.3229 0.08653 0.08248 0.0006 0.6423 0.0197
-6.250 -0.3108 0.08322 0.07911 -0.0006 0.6380 0.0202
-6.000 -0.2960 0.08005 0.07590 -0.0027 0.6330 0.0210
-5.750 -0.2771 0.07720 0.07297 -0.0054 0.6285 0.0237
-5.500 -0.2446 0.07494 0.07051 -0.0120 0.6247 0.0252
-5.250 -0.2211 0.07148 0.06694 -0.0151 0.6199 0.0253
-5.000 -0.1979 0.06792 0.06326 -0.0175 0.6154 0.0254
-4.750 -0.1738 0.06444 0.05962 -0.0196 0.6114 0.0255
-4.250 -0.1445 0.05636 0.05146 -0.0204 0.6029 0.0271
-4.000 -0.1229 0.05370 0.04869 -0.0214 0.5985 0.0284
-3.500 -0.0530 0.05030 0.04477 -0.0254 0.5898 0.0348
-3.250 -0.0254 0.04768 0.04195 -0.0262 0.5855 0.0350
-3.000 -0.0054 0.04298 0.03708 -0.0268 0.5821 0.0358
-2.750 0.0142 0.04034 0.03437 -0.0270 0.5781 0.0369
-2.500 0.0373 0.03848 0.03242 -0.0273 0.5732 0.0391
-2.250 0.0758 0.03812 0.03168 -0.0279 0.5689 0.0469
-2.000 0.1047 0.03632 0.02959 -0.0279 0.5655 0.0472
-1.750 0.1267 0.03261 0.02577 -0.0283 0.5614 0.0484
-1.500 0.1506 0.03080 0.02389 -0.0285 0.5568 0.0498
-1.250 0.1763 0.02952 0.02249 -0.0287 0.5528 0.0529
-1.000 0.2096 0.02846 0.02098 -0.0285 0.5493 0.0609
-0.750 0.2365 0.02562 0.01799 -0.0283 0.5450 0.0446
-0.500 0.2648 0.02386 0.01600 -0.0282 0.5409 0.0416
-0.250 0.2942 0.02202 0.01381 -0.0278 0.5373 0.0395
0.000 0.3236 0.02041 0.01188 -0.0276 0.5336 0.0386
0.250 0.3523 0.01952 0.01083 -0.0277 0.5291 0.0397
0.500 0.3809 0.01873 0.00986 -0.0277 0.5251 0.0412
0.750 0.4098 0.01773 0.00859 -0.0276 0.5216 0.0403
1.000 0.4388 0.01693 0.00760 -0.0276 0.5174 0.0396
1.250 0.4675 0.01631 0.00687 -0.0277 0.5131 0.0392
1.500 0.4956 0.01583 0.00628 -0.0277 0.5093 0.0391
2.000 0.5509 0.01513 0.00549 -0.0277 0.5014 0.0399
2.250 0.5781 0.01487 0.00524 -0.0277 0.4972 0.0406
2.500 0.6051 0.01468 0.00502 -0.0276 0.4936 0.0418
2.750 0.6322 0.01456 0.00487 -0.0275 0.4901 0.0431
3.000 0.6597 0.01449 0.00484 -0.0276 0.4855 0.0457
3.250 0.6867 0.01442 0.00477 -0.0276 0.4813 0.0493
3.500 0.7136 0.01440 0.00471 -0.0275 0.4779 0.0516
3.750 0.7409 0.01443 0.00476 -0.0276 0.4742 0.0555
4.000 0.7684 0.01447 0.00487 -0.0277 0.4697 0.0705
5.000 0.9383 0.01373 0.00587 -0.0416 0.4518 1.0000
5.250 0.9638 0.01390 0.00602 -0.0413 0.4482 1.0000
5.500 0.9894 0.01409 0.00625 -0.0412 0.4443 1.0000
5.750 1.0150 0.01428 0.00651 -0.0411 0.4400 1.0000
6.000 1.0402 0.01443 0.00669 -0.0408 0.4346 1.0000
6.250 1.0654 0.01454 0.00685 -0.0406 0.4235 1.0000
6.500 1.0903 0.01466 0.00698 -0.0404 0.4112 1.0000
6.750 1.1150 0.01482 0.00717 -0.0401 0.3988 1.0000
7.000 1.1395 0.01503 0.00743 -0.0399 0.3857 1.0000
7.250 1.1634 0.01531 0.00771 -0.0397 0.3657 1.0000
7.500 1.1859 0.01576 0.00808 -0.0394 0.3342 1.0000
7.750 1.2033 0.01693 0.00888 -0.0390 0.2657 1.0000
8.000 1.1887 0.02163 0.01231 -0.0369 0.0761 1.0000
8.250 1.1859 0.02408 0.01452 -0.0347 0.0243 1.0000
8.500 1.1945 0.02534 0.01586 -0.0332 0.0208 1.0000
8.750 1.1992 0.02679 0.01746 -0.0316 0.0195 1.0000
9.000 1.1999 0.02850 0.01929 -0.0298 0.0183 1.0000
9.250 1.2014 0.03047 0.02139 -0.0286 0.0170 1.0000
9.500 1.2021 0.03273 0.02377 -0.0277 0.0159 1.0000
9.750 1.2015 0.03524 0.02642 -0.0269 0.0151 1.0000
10.000 1.1991 0.03804 0.02937 -0.0263 0.0146 1.0000
10.250 1.1947 0.04114 0.03262 -0.0258 0.0141 1.0000
10.500 1.1879 0.04456 0.03622 -0.0254 0.0138 1.0000
10.750 1.1804 0.04811 0.03988 -0.0250 0.0135 1.0000
11.000 1.1777 0.05117 0.04305 -0.0247 0.0133 1.0000
11.250 1.1754 0.05419 0.04616 -0.0245 0.0131 1.0000
11.500 1.1739 0.05716 0.04924 -0.0243 0.0127 1.0000
11.750 1.1733 0.06011 0.05227 -0.0241 0.0122 1.0000
12.000 1.1732 0.06304 0.05528 -0.0240 0.0117 1.0000
12.250 1.1734 0.06595 0.05826 -0.0238 0.0112 1.0000
12.500 1.1742 0.06872 0.06110 -0.0235 0.0109 1.0000
12.750 1.1763 0.07129 0.06373 -0.0231 0.0106 1.0000
13.000 1.1800 0.07362 0.06610 -0.0226 0.0104 1.0000
13.250 1.1851 0.07569 0.06825 -0.0219 0.0101 1.0000
13.500 1.1916 0.07750 0.07010 -0.0209 0.0098 1.0000
13.750 1.1998 0.07901 0.07164 -0.0197 0.0096 1.0000
14.000 1.2107 0.08005 0.07269 -0.0180 0.0094 1.0000
14.250 1.2301 0.07966 0.07226 -0.0143 0.0089 1.0000
14.500 1.2320 0.08269 0.07549 -0.0147 0.0087 1.0000
14.750 1.2344 0.08566 0.07866 -0.0151 0.0083 1.0000
15.000 1.2381 0.08845 0.08163 -0.0151 0.0080 1.0000
15.250 1.2416 0.09125 0.08462 -0.0148 0.0078 1.0000
15.500 1.2435 0.09437 0.08794 -0.0148 0.0077 1.0000
15.750 1.2433 0.09784 0.09161 -0.0150 0.0076 1.0000
16.000 1.2410 0.10172 0.09569 -0.0156 0.0075 1.0000
16.250 1.2370 0.10597 0.10015 -0.0165 0.0075 1.0000
16.500 1.2312 0.11061 0.10499 -0.0178 0.0074 1.0000
16.750 1.2238 0.11562 0.11020 -0.0194 0.0074 1.0000
17.000 1.2152 0.12096 0.11574 -0.0215 0.0074 1.0000
17.250 1.2057 0.12665 0.12163 -0.0239 0.0074 1.0000
17.500 1.1954 0.13269 0.12786 -0.0267 0.0074 1.0000
17.750 1.1843 0.13910 0.13447 -0.0299 0.0074 1.0000
18.000 1.1726 0.14591 0.14146 -0.0336 0.0074 1.0000
18.250 1.1604 0.15310 0.14882 -0.0377 0.0075 1.0000
18.500 1.1479 0.16075 0.15663 -0.0422 0.0075 1.0000
18.750 1.1351 0.16888 0.16492 -0.0472 0.0076 1.0000
19.000 1.1223 0.17754 0.17373 -0.0526 0.0077 1.0000
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