NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: NACA 22112 (naca22112-jf) Reynolds number: 200,000 Max Cl/Cd: 49.49 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca22112-jf-200000-n5.txt Download as CSV file: xf-naca22112-jf-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 22112
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7179 0.07905 0.07502 -0.0216 1.0000 0.0203
-11.500 -0.7395 0.07172 0.06757 -0.0273 1.0000 0.0202
-11.250 -0.7616 0.06582 0.06151 -0.0308 1.0000 0.0202
-11.000 -0.7841 0.06092 0.05642 -0.0319 1.0000 0.0201
-10.750 -0.8059 0.05676 0.05205 -0.0306 1.0000 0.0201
-10.500 -0.8250 0.05283 0.04786 -0.0279 1.0000 0.0202
-10.250 -0.8435 0.04770 0.04226 -0.0248 1.0000 0.0204
-10.000 -0.8366 0.04593 0.04039 -0.0233 1.0000 0.0207
-9.750 -0.8251 0.04467 0.03907 -0.0220 1.0000 0.0210
-9.500 -0.8144 0.04308 0.03735 -0.0206 1.0000 0.0214
-9.250 -0.8048 0.04103 0.03512 -0.0189 1.0000 0.0218
-9.000 -0.7955 0.03854 0.03235 -0.0169 1.0000 0.0223
-8.750 -0.7854 0.03580 0.02928 -0.0148 1.0000 0.0227
-8.500 -0.7733 0.03316 0.02629 -0.0126 1.0000 0.0231
-8.250 -0.7591 0.03067 0.02344 -0.0106 1.0000 0.0236
-8.000 -0.7431 0.02838 0.02074 -0.0086 1.0000 0.0242
-7.750 -0.7246 0.02693 0.01913 -0.0071 1.0000 0.0247
-7.500 -0.7051 0.02613 0.01831 -0.0059 1.0000 0.0253
-7.250 -0.6854 0.02531 0.01743 -0.0045 1.0000 0.0261
-7.000 -0.6656 0.02431 0.01631 -0.0031 1.0000 0.0270
-6.750 -0.6452 0.02314 0.01499 -0.0016 1.0000 0.0278
-6.500 -0.6247 0.02203 0.01372 -0.0001 1.0000 0.0285
-6.250 -0.6044 0.02104 0.01264 0.0014 1.0000 0.0292
-6.000 -0.5848 0.02028 0.01191 0.0028 1.0000 0.0299
-5.750 -0.5653 0.01972 0.01135 0.0043 1.0000 0.0309
-5.500 -0.5458 0.01916 0.01077 0.0059 1.0000 0.0322
-5.250 -0.5174 0.01844 0.00998 0.0057 0.9974 0.0337
-5.000 -0.4824 0.01757 0.00911 0.0040 0.9925 0.0349
-4.750 -0.4477 0.01686 0.00845 0.0024 0.9864 0.0364
-4.500 -0.4121 0.01630 0.00789 0.0006 0.9802 0.0387
-4.250 -0.3770 0.01573 0.00729 -0.0009 0.9730 0.0410
-4.000 -0.3447 0.01508 0.00669 -0.0020 0.9639 0.0431
-3.750 -0.3099 0.01460 0.00620 -0.0035 0.9554 0.0462
-3.500 -0.2785 0.01414 0.00572 -0.0041 0.9433 0.0497
-3.250 -0.2471 0.01372 0.00529 -0.0047 0.9304 0.0537
-3.000 -0.2158 0.01337 0.00489 -0.0053 0.9164 0.0592
-2.750 -0.1857 0.01300 0.00451 -0.0055 0.9005 0.0676
-2.500 -0.1574 0.01254 0.00412 -0.0053 0.8824 0.0888
-2.250 -0.1417 0.01075 0.00364 -0.0037 0.8623 0.3940
-2.000 -0.1198 0.01012 0.00348 -0.0023 0.8413 0.5149
-1.750 -0.0976 0.00971 0.00339 -0.0006 0.8182 0.6066
-1.500 -0.0741 0.00948 0.00334 0.0009 0.7941 0.6700
-1.250 -0.0501 0.00935 0.00332 0.0024 0.7687 0.7265
-1.000 -0.0257 0.00931 0.00333 0.0039 0.7412 0.7761
-0.750 -0.0008 0.00937 0.00338 0.0054 0.7079 0.8203
-0.500 0.0252 0.00952 0.00342 0.0066 0.6704 0.8507
-0.250 0.0524 0.00968 0.00341 0.0072 0.6343 0.8688
0.000 0.0807 0.00985 0.00343 0.0076 0.6042 0.8835
0.250 0.1097 0.01001 0.00345 0.0077 0.5759 0.8970
0.500 0.1385 0.01019 0.00348 0.0078 0.5481 0.9100
0.750 0.1692 0.01039 0.00353 0.0075 0.5187 0.9210
1.000 0.2006 0.01061 0.00359 0.0069 0.4889 0.9306
1.250 0.2301 0.01081 0.00365 0.0067 0.4611 0.9414
1.500 0.2646 0.01104 0.00373 0.0054 0.4317 0.9482
1.750 0.2952 0.01128 0.00381 0.0049 0.4021 0.9571
2.000 0.3308 0.01154 0.00391 0.0033 0.3705 0.9626
2.250 0.3624 0.01181 0.00402 0.0024 0.3419 0.9704
2.500 0.3997 0.01207 0.00414 0.0003 0.3131 0.9744
2.750 0.4343 0.01235 0.00428 -0.0013 0.2859 0.9801
3.250 0.5046 0.01292 0.00459 -0.0048 0.2396 0.9896
3.500 0.5391 0.01321 0.00479 -0.0065 0.2230 0.9943
3.750 0.5750 0.01348 0.00498 -0.0085 0.2087 0.9981
4.250 0.6257 0.01399 0.00539 -0.0079 0.1894 1.0000
4.500 0.6472 0.01428 0.00562 -0.0069 0.1826 1.0000
4.750 0.6691 0.01452 0.00586 -0.0059 0.1769 1.0000
5.000 0.6907 0.01480 0.00612 -0.0048 0.1712 1.0000
5.250 0.7118 0.01514 0.00641 -0.0037 0.1662 1.0000
5.500 0.7338 0.01540 0.00671 -0.0027 0.1616 1.0000
5.750 0.7554 0.01570 0.00702 -0.0016 0.1575 1.0000
6.000 0.7764 0.01608 0.00737 -0.0004 0.1536 1.0000
6.250 0.7978 0.01643 0.00773 0.0007 0.1499 1.0000
6.500 0.8197 0.01675 0.00810 0.0017 0.1461 1.0000
6.750 0.8412 0.01711 0.00849 0.0027 0.1427 1.0000
7.000 0.8621 0.01753 0.00889 0.0038 0.1394 1.0000
7.250 0.8831 0.01798 0.00934 0.0049 0.1363 1.0000
7.500 0.9051 0.01833 0.00979 0.0059 0.1331 1.0000
7.750 0.9268 0.01873 0.01024 0.0069 0.1299 1.0000
8.000 0.9482 0.01916 0.01069 0.0078 0.1268 1.0000
8.250 0.9687 0.01971 0.01121 0.0089 0.1238 1.0000
8.500 0.9907 0.02013 0.01175 0.0097 0.1210 1.0000
8.750 1.0126 0.02057 0.01228 0.0106 0.1178 1.0000
9.000 1.0341 0.02101 0.01279 0.0114 0.1147 1.0000
9.250 1.0547 0.02152 0.01332 0.0123 0.1118 1.0000
9.500 1.0753 0.02210 0.01395 0.0133 0.1091 1.0000
9.750 1.0966 0.02258 0.01457 0.0141 0.1059 1.0000
10.000 1.1172 0.02307 0.01516 0.0150 0.1027 1.0000
10.250 1.1367 0.02359 0.01572 0.0159 0.0999 1.0000
10.500 1.1555 0.02423 0.01641 0.0169 0.0971 1.0000
10.750 1.1751 0.02479 0.01713 0.0179 0.0938 1.0000
11.000 1.1936 0.02535 0.01780 0.0189 0.0906 1.0000
11.250 1.2103 0.02598 0.01846 0.0201 0.0878 1.0000
11.500 1.2266 0.02670 0.01929 0.0213 0.0849 1.0000
11.750 1.2428 0.02740 0.02014 0.0225 0.0817 1.0000
12.000 1.2559 0.02811 0.02094 0.0240 0.0788 1.0000
12.250 1.2652 0.02898 0.02182 0.0259 0.0763 1.0000
12.500 1.2772 0.02989 0.02292 0.0274 0.0734 1.0000
12.750 1.2874 0.03089 0.02404 0.0289 0.0705 1.0000
13.000 1.2951 0.03206 0.02528 0.0302 0.0680 1.0000
13.250 1.3015 0.03346 0.02678 0.0314 0.0657 1.0000
13.500 1.3088 0.03495 0.02845 0.0322 0.0630 1.0000
13.750 1.3135 0.03669 0.03030 0.0328 0.0605 1.0000
14.000 1.3151 0.03884 0.03252 0.0330 0.0585 1.0000
14.250 1.3165 0.04123 0.03506 0.0330 0.0565 1.0000
14.500 1.3170 0.04390 0.03790 0.0325 0.0544 1.0000
14.750 1.3145 0.04708 0.04122 0.0315 0.0525 1.0000
15.000 1.3083 0.05090 0.04514 0.0300 0.0510 1.0000
15.250 1.2991 0.05534 0.04969 0.0279 0.0499 1.0000
15.500 1.2897 0.06003 0.05458 0.0257 0.0485 1.0000
15.750 1.2762 0.06547 0.06021 0.0230 0.0474 1.0000
16.000 1.2590 0.07166 0.06656 0.0197 0.0465 1.0000
16.250 1.2378 0.07863 0.07369 0.0160 0.0458 1.0000
16.500 1.2135 0.08637 0.08157 0.0119 0.0452 1.0000
16.750 1.1865 0.09478 0.09013 0.0074 0.0448 1.0000
17.000 1.1584 0.10367 0.09913 0.0027 0.0443 1.0000
17.250 1.1317 0.11245 0.10802 -0.0019 0.0438 1.0000
17.500 1.1113 0.12017 0.11578 -0.0060 0.0430 1.0000
17.750 1.0764 0.13122 0.12699 -0.0120 0.0424 1.0000
18.000 1.0235 0.14680 0.14276 -0.0205 0.0415 1.0000
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