NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 22112 (naca22112-jf) Reynolds number: 200,000 Max Cl/Cd: 45.69 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca22112-jf-200000.txt Download as CSV file: xf-naca22112-jf-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6436 0.09512 0.09139 -0.0193 1.0000 0.0573
-10.750 -0.6721 0.08814 0.08431 -0.0258 1.0000 0.0574
-10.500 -0.7004 0.08350 0.07955 -0.0281 1.0000 0.0574
-10.250 -0.7290 0.08030 0.07619 -0.0271 1.0000 0.0575
-10.000 -0.7500 0.07755 0.07319 -0.0256 1.0000 0.0577
-9.750 -0.7411 0.06901 0.06480 -0.0268 1.0000 0.0589
-9.500 -0.7242 0.06552 0.06142 -0.0267 1.0000 0.0600
-9.250 -0.7192 0.06255 0.05842 -0.0259 1.0000 0.0611
-9.000 -0.7181 0.05953 0.05529 -0.0248 1.0000 0.0626
-8.750 -0.7183 0.05652 0.05210 -0.0233 1.0000 0.0648
-8.250 -0.7263 0.04991 0.04476 -0.0185 1.0000 0.0709
-8.000 -0.7107 0.04702 0.04195 -0.0178 1.0000 0.0728
-7.750 -0.6983 0.04499 0.03982 -0.0162 1.0000 0.0766
-7.500 -0.6983 0.04271 0.03707 -0.0128 1.0000 0.0840
-7.250 -0.6816 0.04009 0.03456 -0.0119 1.0000 0.0871
-6.250 -0.6180 0.02864 0.02128 0.0000 1.0000 0.0552
-6.000 -0.5993 0.02673 0.01917 0.0020 1.0000 0.0545
-5.750 -0.5794 0.02501 0.01726 0.0038 1.0000 0.0539
-5.500 -0.5583 0.02336 0.01543 0.0055 1.0000 0.0529
-5.250 -0.5370 0.02206 0.01399 0.0071 1.0000 0.0527
-5.000 -0.5159 0.02099 0.01284 0.0085 1.0000 0.0534
-4.750 -0.4953 0.02023 0.01201 0.0100 1.0000 0.0552
-4.500 -0.4748 0.01957 0.01128 0.0115 1.0000 0.0566
-4.250 -0.4542 0.01896 0.01059 0.0130 1.0000 0.0575
-4.000 -0.4335 0.01780 0.00949 0.0143 1.0000 0.0589
-3.750 -0.4144 0.01696 0.00876 0.0156 1.0000 0.0613
-3.500 -0.3704 0.01623 0.00808 0.0122 0.9946 0.0659
-3.250 -0.3274 0.01553 0.00739 0.0091 0.9877 0.0694
-3.000 -0.2854 0.01459 0.00653 0.0059 0.9809 0.0771
-2.750 -0.2423 0.01392 0.00586 0.0028 0.9728 0.0869
-2.500 -0.2058 0.01243 0.00512 0.0005 0.9638 0.2394
-2.250 -0.1773 0.01036 0.00497 0.0001 0.9563 0.6473
-2.000 -0.1458 0.00998 0.00501 0.0005 0.9439 0.7526
-1.750 -0.1130 0.00986 0.00505 0.0008 0.9309 0.8109
-1.500 -0.0805 0.00984 0.00509 0.0012 0.9165 0.8490
-1.250 -0.0496 0.00989 0.00515 0.0021 0.8996 0.8792
-1.000 -0.0188 0.01002 0.00524 0.0031 0.8799 0.9041
-0.750 0.0130 0.01022 0.00535 0.0041 0.8558 0.9257
-0.500 0.0499 0.01040 0.00538 0.0036 0.8261 0.9389
-0.250 0.0901 0.01051 0.00533 0.0019 0.7954 0.9462
0.000 0.1262 0.01063 0.00529 0.0008 0.7658 0.9566
0.250 0.1708 0.01074 0.00523 -0.0022 0.7336 0.9622
0.500 0.2082 0.01087 0.00517 -0.0039 0.7001 0.9715
0.750 0.2510 0.01099 0.00509 -0.0067 0.6643 0.9782
1.000 0.2916 0.01110 0.00502 -0.0093 0.6289 0.9856
1.250 0.3334 0.01122 0.00493 -0.0122 0.5914 0.9925
1.500 0.3764 0.01131 0.00482 -0.0155 0.5514 0.9982
1.750 0.4056 0.01140 0.00474 -0.0161 0.5156 1.0000
2.000 0.4286 0.01151 0.00468 -0.0154 0.4824 1.0000
2.250 0.4515 0.01166 0.00466 -0.0148 0.4478 1.0000
2.500 0.4743 0.01186 0.00467 -0.0141 0.4114 1.0000
2.750 0.4968 0.01211 0.00471 -0.0133 0.3743 1.0000
3.000 0.5191 0.01240 0.00481 -0.0126 0.3381 1.0000
3.250 0.5410 0.01275 0.00496 -0.0117 0.3068 1.0000
3.500 0.5627 0.01310 0.00516 -0.0108 0.2811 1.0000
3.750 0.5841 0.01348 0.00538 -0.0098 0.2619 1.0000
4.000 0.6056 0.01384 0.00563 -0.0087 0.2468 1.0000
4.250 0.6274 0.01418 0.00593 -0.0077 0.2350 1.0000
4.500 0.6486 0.01461 0.00625 -0.0066 0.2258 1.0000
4.750 0.6704 0.01494 0.00656 -0.0056 0.2172 1.0000
5.000 0.6918 0.01539 0.00694 -0.0045 0.2100 1.0000
5.250 0.7136 0.01573 0.00729 -0.0034 0.2032 1.0000
5.500 0.7350 0.01631 0.00775 -0.0023 0.1976 1.0000
5.750 0.7571 0.01666 0.00817 -0.0013 0.1923 1.0000
6.000 0.7790 0.01705 0.00857 -0.0003 0.1868 1.0000
6.250 0.8010 0.01777 0.00915 0.0006 0.1819 1.0000
6.500 0.8231 0.01813 0.00964 0.0017 0.1778 1.0000
6.750 0.8452 0.01857 0.01013 0.0027 0.1732 1.0000
7.000 0.8674 0.01912 0.01062 0.0036 0.1689 1.0000
7.250 0.8897 0.01985 0.01138 0.0044 0.1650 1.0000
7.500 0.9115 0.02032 0.01197 0.0055 0.1609 1.0000
7.750 0.9336 0.02081 0.01250 0.0064 0.1568 1.0000
8.000 0.9564 0.02159 0.01320 0.0070 0.1530 1.0000
8.250 0.9781 0.02232 0.01407 0.0079 0.1495 1.0000
8.500 0.9995 0.02286 0.01476 0.0089 0.1455 1.0000
8.750 1.0215 0.02340 0.01533 0.0097 0.1417 1.0000
9.000 1.0445 0.02442 0.01627 0.0101 0.1380 1.0000
9.250 1.0646 0.02511 0.01719 0.0112 0.1346 1.0000
9.500 1.0849 0.02570 0.01793 0.0123 0.1307 1.0000
9.750 1.1064 0.02625 0.01851 0.0130 0.1271 1.0000
10.000 1.1285 0.02753 0.01972 0.0134 0.1233 1.0000
10.250 1.1459 0.02807 0.02054 0.0148 0.1201 1.0000
10.500 1.1644 0.02866 0.02129 0.0159 0.1162 1.0000
10.750 1.1852 0.02913 0.02173 0.0167 0.1128 1.0000
11.000 1.2039 0.03032 0.02297 0.0175 0.1094 1.0000
11.250 1.2179 0.03102 0.02395 0.0191 0.1058 1.0000
11.500 1.2348 0.03154 0.02456 0.0203 0.1023 1.0000
11.750 1.2546 0.03205 0.02497 0.0210 0.0991 1.0000
12.000 1.2655 0.03326 0.02642 0.0227 0.0959 1.0000
12.250 1.2755 0.03408 0.02746 0.0246 0.0925 1.0000
12.500 1.2898 0.03450 0.02788 0.0259 0.0894 1.0000
12.750 1.3041 0.03560 0.02893 0.0270 0.0864 1.0000
13.000 1.3016 0.03681 0.03045 0.0302 0.0839 1.0000
13.250 1.3034 0.03794 0.03174 0.0324 0.0812 1.0000
13.500 1.3114 0.03872 0.03253 0.0338 0.0786 1.0000
13.750 1.3198 0.04015 0.03389 0.0349 0.0760 1.0000
14.000 1.3112 0.04244 0.03651 0.0364 0.0740 1.0000
14.250 1.3066 0.04477 0.03904 0.0370 0.0718 1.0000
14.500 1.3085 0.04664 0.04098 0.0371 0.0695 1.0000
14.750 1.3163 0.04818 0.04243 0.0373 0.0672 1.0000
15.000 1.3052 0.05196 0.04643 0.0366 0.0656 1.0000
15.250 1.2899 0.05653 0.05128 0.0349 0.0643 1.0000
15.500 1.2757 0.06131 0.05627 0.0327 0.0628 1.0000
15.750 1.2652 0.06584 0.06094 0.0304 0.0613 1.0000
16.000 1.2655 0.06883 0.06393 0.0290 0.0596 1.0000
16.250 1.2649 0.07190 0.06695 0.0283 0.0578 1.0000
16.500 1.2367 0.07964 0.07496 0.0237 0.0574 1.0000
16.750 1.2027 0.08891 0.08447 0.0181 0.0571 1.0000
17.000 1.1575 0.10081 0.09662 0.0109 0.0572 1.0000
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