NACA 25112 (naca25112-jf) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 25112 (naca25112-jf) Reynolds number: 200,000 Max Cl/Cd: 63.88 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca25112-jf-200000-n5.txt Download as CSV file: xf-naca25112-jf-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 25112
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5903 0.09133 0.08770 -0.0062 1.0000 0.0247
-10.250 -0.6121 0.08179 0.07820 -0.0131 1.0000 0.0247
-10.000 -0.6832 0.06359 0.05986 -0.0266 1.0000 0.0243
-9.750 -0.7782 0.04325 0.03855 -0.0257 1.0000 0.0247
-9.500 -0.7870 0.03775 0.03247 -0.0232 1.0000 0.0255
-9.250 -0.7889 0.03287 0.02686 -0.0204 1.0000 0.0265
-9.000 -0.7781 0.03009 0.02360 -0.0185 1.0000 0.0272
-8.750 -0.7591 0.02899 0.02243 -0.0175 1.0000 0.0277
-8.500 -0.7398 0.02787 0.02120 -0.0164 1.0000 0.0283
-8.250 -0.7205 0.02664 0.01980 -0.0152 1.0000 0.0290
-8.000 -0.7010 0.02532 0.01827 -0.0139 1.0000 0.0300
-7.750 -0.6811 0.02397 0.01662 -0.0126 1.0000 0.0312
-7.500 -0.6605 0.02293 0.01545 -0.0115 1.0000 0.0322
-7.250 -0.6396 0.02228 0.01479 -0.0103 1.0000 0.0331
-7.000 -0.6183 0.02154 0.01399 -0.0092 0.9994 0.0342
-6.750 -0.5835 0.02051 0.01278 -0.0108 0.9858 0.0357
-6.500 -0.5488 0.01955 0.01165 -0.0123 0.9695 0.0375
-6.250 -0.5155 0.01894 0.01106 -0.0136 0.9495 0.0391
-6.000 -0.4826 0.01830 0.01032 -0.0146 0.9268 0.0412
-5.750 -0.4523 0.01762 0.00947 -0.0149 0.9014 0.0431
-5.500 -0.4253 0.01708 0.00891 -0.0145 0.8745 0.0451
-5.250 -0.3997 0.01670 0.00843 -0.0138 0.8470 0.0476
-5.000 -0.3749 0.01629 0.00785 -0.0128 0.8207 0.0501
-4.750 -0.3509 0.01585 0.00735 -0.0118 0.7952 0.0525
-4.500 -0.3263 0.01557 0.00695 -0.0109 0.7712 0.0558
-4.250 -0.3013 0.01526 0.00650 -0.0101 0.7483 0.0593
-4.000 -0.2767 0.01493 0.00612 -0.0093 0.7265 0.0629
-3.750 -0.2513 0.01470 0.00576 -0.0086 0.7060 0.0676
-3.500 -0.2263 0.01441 0.00542 -0.0079 0.6868 0.0725
-3.250 -0.2006 0.01422 0.00512 -0.0073 0.6686 0.0785
-2.750 -0.1491 0.01380 0.00457 -0.0062 0.6351 0.0934
-2.500 -0.1233 0.01360 0.00434 -0.0057 0.6198 0.1036
-2.250 -0.0974 0.01341 0.00413 -0.0053 0.6053 0.1157
-2.000 -0.0714 0.01323 0.00394 -0.0048 0.5918 0.1313
-1.750 -0.0454 0.01306 0.00377 -0.0044 0.5794 0.1522
-1.500 -0.0199 0.01285 0.00361 -0.0039 0.5675 0.1823
-1.250 0.0050 0.01253 0.00346 -0.0034 0.5560 0.2363
-1.000 0.0172 0.01105 0.00322 -0.0008 0.5470 0.5581
-0.750 0.0379 0.01037 0.00346 0.0018 0.5370 0.8055
-0.500 0.0743 0.01054 0.00369 0.0010 0.5265 0.8766
-0.250 0.1084 0.01078 0.00382 0.0003 0.5169 0.9088
0.000 0.1446 0.01100 0.00397 -0.0009 0.5068 0.9291
0.250 0.1807 0.01124 0.00408 -0.0022 0.4979 0.9446
0.500 0.2193 0.01146 0.00421 -0.0040 0.4884 0.9573
0.750 0.2665 0.01170 0.00434 -0.0078 0.4791 0.9688
1.000 0.3160 0.01188 0.00441 -0.0121 0.4696 0.9786
1.250 0.3506 0.01197 0.00442 -0.0136 0.4616 0.9838
1.500 0.3854 0.01201 0.00439 -0.0151 0.4534 0.9864
1.750 0.4192 0.01207 0.00439 -0.0165 0.4460 0.9896
2.000 0.4520 0.01214 0.00441 -0.0176 0.4381 0.9928
2.250 0.4859 0.01222 0.00442 -0.0190 0.4308 0.9954
2.500 0.5198 0.01227 0.00445 -0.0205 0.4229 0.9979
2.750 0.5518 0.01237 0.00448 -0.0215 0.4160 1.0000
3.000 0.5768 0.01243 0.00455 -0.0211 0.4088 1.0000
3.250 0.6014 0.01253 0.00461 -0.0205 0.4022 1.0000
3.500 0.6260 0.01263 0.00471 -0.0200 0.3954 1.0000
3.750 0.6504 0.01274 0.00481 -0.0194 0.3885 1.0000
4.000 0.6746 0.01287 0.00492 -0.0188 0.3821 1.0000
4.250 0.6989 0.01299 0.00506 -0.0182 0.3748 1.0000
4.750 0.7469 0.01329 0.00536 -0.0169 0.3611 1.0000
5.000 0.7705 0.01346 0.00551 -0.0162 0.3543 1.0000
5.250 0.7943 0.01362 0.00571 -0.0155 0.3472 1.0000
5.500 0.8177 0.01380 0.00590 -0.0148 0.3398 1.0000
5.750 0.8411 0.01400 0.00611 -0.0140 0.3326 1.0000
6.000 0.8642 0.01419 0.00633 -0.0132 0.3248 1.0000
6.250 0.8872 0.01441 0.00657 -0.0124 0.3172 1.0000
6.500 0.9099 0.01463 0.00681 -0.0116 0.3088 1.0000
6.750 0.9326 0.01487 0.00709 -0.0107 0.3005 1.0000
7.000 0.9547 0.01513 0.00735 -0.0098 0.2915 1.0000
7.250 0.9770 0.01538 0.00765 -0.0089 0.2817 1.0000
7.500 0.9986 0.01567 0.00796 -0.0079 0.2718 1.0000
7.750 1.0199 0.01599 0.00828 -0.0069 0.2609 1.0000
8.000 1.0413 0.01630 0.00863 -0.0059 0.2494 1.0000
8.250 1.0620 0.01666 0.00900 -0.0049 0.2377 1.0000
8.500 1.0821 0.01706 0.00942 -0.0037 0.2255 1.0000
8.750 1.1015 0.01750 0.00985 -0.0025 0.2126 1.0000
9.000 1.1204 0.01799 0.01033 -0.0013 0.1992 1.0000
9.250 1.1386 0.01853 0.01087 0.0000 0.1852 1.0000
9.500 1.1561 0.01912 0.01145 0.0013 0.1708 1.0000
9.750 1.1728 0.01977 0.01209 0.0027 0.1561 1.0000
10.000 1.1884 0.02050 0.01280 0.0042 0.1416 1.0000
10.250 1.2027 0.02130 0.01359 0.0058 0.1273 1.0000
10.500 1.2157 0.02218 0.01445 0.0074 0.1143 1.0000
10.750 1.2272 0.02314 0.01539 0.0092 0.1024 1.0000
11.000 1.2365 0.02418 0.01643 0.0111 0.0921 1.0000
11.250 1.2428 0.02527 0.01754 0.0134 0.0836 1.0000
11.500 1.2477 0.02643 0.01875 0.0157 0.0766 1.0000
11.750 1.2504 0.02791 0.02025 0.0176 0.0707 1.0000
12.000 1.2543 0.02952 0.02192 0.0188 0.0653 1.0000
12.250 1.2557 0.03153 0.02399 0.0197 0.0611 1.0000
12.500 1.2584 0.03364 0.02620 0.0200 0.0572 1.0000
12.750 1.2574 0.03632 0.02894 0.0199 0.0540 1.0000
13.000 1.2579 0.03902 0.03175 0.0196 0.0512 1.0000
13.250 1.2570 0.04199 0.03482 0.0190 0.0487 1.0000
13.500 1.2530 0.04544 0.03835 0.0182 0.0467 1.0000
13.750 1.2480 0.04907 0.04206 0.0172 0.0450 1.0000
14.000 1.2450 0.05249 0.04561 0.0163 0.0432 1.0000
14.250 1.2397 0.05622 0.04944 0.0153 0.0417 1.0000
14.500 1.2327 0.06022 0.05353 0.0141 0.0403 1.0000
14.750 1.2235 0.06452 0.05790 0.0128 0.0393 1.0000
15.000 1.2161 0.06865 0.06212 0.0115 0.0382 1.0000
15.250 1.2109 0.07258 0.06618 0.0103 0.0371 1.0000
15.500 1.2051 0.07670 0.07040 0.0090 0.0360 1.0000
15.750 1.1989 0.08098 0.07478 0.0075 0.0350 1.0000
16.000 1.1920 0.08542 0.07928 0.0058 0.0341 1.0000
16.250 1.1846 0.08996 0.08387 0.0042 0.0333 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 25112 (naca25112-jf)