LA2573A (la2573a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: LA2573A (la2573a-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.9 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-la2573a-il-1000000-n5.txt Download as CSV file: xf-la2573a-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LA2573A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -1.1785 0.04691 0.04308 -0.0278 0.5242 0.0208
-14.500 -1.2119 0.04181 0.03775 -0.0273 0.5213 0.0208
-14.250 -1.2288 0.03877 0.03453 -0.0250 0.5161 0.0209
-14.000 -1.2374 0.03662 0.03221 -0.0222 0.5092 0.0210
-13.750 -1.2449 0.03468 0.03010 -0.0187 0.5038 0.0210
-13.500 -1.2453 0.03318 0.02845 -0.0155 0.4987 0.0211
-13.250 -1.2389 0.03163 0.02674 -0.0133 0.4929 0.0212
-12.750 -1.2161 0.02901 0.02381 -0.0097 0.4827 0.0215
-12.500 -1.2017 0.02782 0.02248 -0.0081 0.4786 0.0216
-12.250 -1.1857 0.02673 0.02124 -0.0067 0.4743 0.0217
-12.000 -1.1681 0.02574 0.02011 -0.0054 0.4701 0.0218
-11.500 -1.1290 0.02404 0.01815 -0.0031 0.4632 0.0221
-11.250 -1.1080 0.02328 0.01728 -0.0020 0.4605 0.0222
-11.000 -1.0862 0.02261 0.01650 -0.0011 0.4575 0.0223
-10.750 -1.0649 0.02182 0.01560 -0.0001 0.4542 0.0224
-10.500 -1.0439 0.02096 0.01463 0.0010 0.4510 0.0225
-10.250 -1.0214 0.02028 0.01387 0.0019 0.4477 0.0227
-10.000 -0.9979 0.01972 0.01324 0.0027 0.4452 0.0228
-9.750 -0.9738 0.01921 0.01268 0.0034 0.4437 0.0230
-9.500 -0.9494 0.01872 0.01213 0.0041 0.4419 0.0231
-9.250 -0.9245 0.01827 0.01163 0.0048 0.4400 0.0232
-9.000 -0.8994 0.01785 0.01115 0.0054 0.4380 0.0234
-8.750 -0.8740 0.01744 0.01068 0.0060 0.4360 0.0236
-8.500 -0.8485 0.01703 0.01022 0.0066 0.4340 0.0237
-8.250 -0.8228 0.01664 0.00976 0.0072 0.4319 0.0239
-8.000 -0.7970 0.01625 0.00931 0.0077 0.4298 0.0241
-7.750 -0.7710 0.01587 0.00887 0.0083 0.4273 0.0243
-7.500 -0.7448 0.01550 0.00845 0.0088 0.4258 0.0245
-7.250 -0.7185 0.01513 0.00803 0.0093 0.4246 0.0247
-7.000 -0.6920 0.01479 0.00764 0.0098 0.4234 0.0249
-6.750 -0.6653 0.01446 0.00726 0.0102 0.4221 0.0252
-6.500 -0.6384 0.01417 0.00693 0.0107 0.4207 0.0254
-6.250 -0.6113 0.01390 0.00662 0.0111 0.4192 0.0255
-6.000 -0.5848 0.01354 0.00621 0.0116 0.4177 0.0258
-5.750 -0.5580 0.01320 0.00585 0.0120 0.4163 0.0261
-5.500 -0.5309 0.01293 0.00556 0.0124 0.4146 0.0263
-5.250 -0.5036 0.01270 0.00531 0.0128 0.4129 0.0266
-5.000 -0.4762 0.01248 0.00507 0.0131 0.4110 0.0269
-4.750 -0.4487 0.01228 0.00484 0.0135 0.4091 0.0272
-4.500 -0.4211 0.01208 0.00462 0.0138 0.4079 0.0275
-4.250 -0.3935 0.01187 0.00440 0.0142 0.4071 0.0278
-4.000 -0.3657 0.01167 0.00419 0.0145 0.4063 0.0282
-3.750 -0.3380 0.01148 0.00398 0.0148 0.4053 0.0286
-3.500 -0.3101 0.01130 0.00379 0.0151 0.4041 0.0289
-3.250 -0.2821 0.01114 0.00361 0.0154 0.4027 0.0291
-3.000 -0.2545 0.01092 0.00339 0.0157 0.4012 0.0296
-2.750 -0.2266 0.01075 0.00323 0.0160 0.3999 0.0301
-2.500 -0.1985 0.01062 0.00310 0.0162 0.3986 0.0307
-2.250 -0.1703 0.01050 0.00297 0.0164 0.3973 0.0314
-2.000 -0.1422 0.01038 0.00284 0.0167 0.3959 0.0320
-1.750 -0.1139 0.01027 0.00272 0.0169 0.3944 0.0326
-1.500 -0.0857 0.01018 0.00261 0.0171 0.3926 0.0330
-1.250 -0.0577 0.01006 0.00249 0.0173 0.3908 0.0339
-1.000 -0.0294 0.00994 0.00240 0.0175 0.3902 0.0348
-0.750 -0.0009 0.00985 0.00232 0.0177 0.3893 0.0357
-0.500 0.0275 0.00976 0.00225 0.0179 0.3883 0.0366
-0.250 0.0560 0.00967 0.00217 0.0180 0.3871 0.0378
0.000 0.0844 0.00958 0.00211 0.0182 0.3857 0.0395
0.250 0.1130 0.00951 0.00206 0.0183 0.3843 0.0412
0.500 0.1414 0.00944 0.00200 0.0185 0.3830 0.0433
0.750 0.1700 0.00938 0.00197 0.0186 0.3816 0.0460
1.000 0.1985 0.00932 0.00193 0.0187 0.3802 0.0499
1.250 0.2270 0.00927 0.00190 0.0188 0.3786 0.0559
1.750 0.2836 0.00915 0.00188 0.0191 0.3750 0.0852
2.000 0.3116 0.00903 0.00189 0.0192 0.3739 0.1202
2.250 0.3389 0.00880 0.00189 0.0194 0.3728 0.1965
2.500 0.3452 0.00675 0.00184 0.0233 0.3718 0.8295
2.750 0.3716 0.00673 0.00194 0.0240 0.3702 0.8726
3.000 0.3992 0.00677 0.00201 0.0244 0.3687 0.8900
3.250 0.4266 0.00682 0.00208 0.0249 0.3671 0.9048
3.500 0.4530 0.00687 0.00216 0.0257 0.3651 0.9197
3.750 0.4787 0.00693 0.00225 0.0266 0.3633 0.9330
4.000 0.5072 0.00700 0.00229 0.0267 0.3614 0.9360
4.250 0.5362 0.00707 0.00234 0.0266 0.3591 0.9374
4.500 0.5653 0.00712 0.00239 0.0265 0.3576 0.9388
4.750 0.5944 0.00717 0.00244 0.0264 0.3558 0.9401
5.000 0.6236 0.00721 0.00250 0.0263 0.3535 0.9414
5.250 0.6528 0.00726 0.00255 0.0262 0.3510 0.9428
5.500 0.6818 0.00732 0.00261 0.0261 0.3484 0.9443
5.750 0.7106 0.00740 0.00268 0.0261 0.3456 0.9460
6.000 0.7394 0.00748 0.00276 0.0260 0.3429 0.9477
6.250 0.7683 0.00754 0.00284 0.0259 0.3404 0.9496
6.500 0.7970 0.00761 0.00293 0.0258 0.3369 0.9516
6.750 0.8254 0.00770 0.00301 0.0258 0.3329 0.9538
7.250 0.8822 0.00796 0.00321 0.0256 0.3133 0.9582
7.500 0.9101 0.00821 0.00338 0.0254 0.2928 0.9604
7.750 0.9382 0.00846 0.00359 0.0252 0.2795 0.9629
8.000 0.9659 0.00874 0.00382 0.0251 0.2663 0.9657
8.250 0.9932 0.00906 0.00409 0.0250 0.2523 0.9689
8.500 1.0213 0.00947 0.00443 0.0245 0.2340 0.9715
8.750 1.0495 0.01004 0.00490 0.0239 0.2111 0.9741
9.000 1.0773 0.01071 0.00544 0.0232 0.1868 0.9773
9.250 1.1044 0.01142 0.00604 0.0225 0.1627 0.9808
9.500 1.1322 0.01226 0.00675 0.0214 0.1374 0.9838
9.750 1.1600 0.01325 0.00760 0.0201 0.1115 0.9865
10.000 1.1876 0.01420 0.00844 0.0187 0.0912 0.9897
10.250 1.2148 0.01506 0.00923 0.0176 0.0770 0.9932
10.750 1.2580 0.01668 0.01078 0.0173 0.0602 1.0000
11.000 1.2732 0.01747 0.01156 0.0184 0.0547 1.0000
11.250 1.2875 0.01834 0.01244 0.0193 0.0503 1.0000
11.500 1.2990 0.01942 0.01353 0.0202 0.0465 1.0000
11.750 1.3065 0.02086 0.01502 0.0208 0.0439 1.0000
12.250 1.2917 0.02814 0.02249 0.0181 0.0411 1.0000
12.500 1.2880 0.03125 0.02565 0.0175 0.0398 1.0000
12.750 1.2823 0.03446 0.02892 0.0169 0.0385 1.0000
13.000 1.2769 0.03760 0.03209 0.0164 0.0374 1.0000
13.250 1.2735 0.04051 0.03506 0.0159 0.0365 1.0000
13.500 1.2705 0.04336 0.03796 0.0155 0.0355 1.0000
13.750 1.2675 0.04621 0.04085 0.0151 0.0346 1.0000
14.000 1.2640 0.04913 0.04381 0.0146 0.0338 1.0000
14.250 1.2632 0.05188 0.04660 0.0142 0.0328 1.0000
14.500 1.2649 0.05444 0.04920 0.0137 0.0322 1.0000
14.750 1.2657 0.05716 0.05196 0.0132 0.0316 1.0000
15.000 1.2674 0.05977 0.05460 0.0127 0.0306 1.0000
15.250 1.2680 0.06257 0.05745 0.0121 0.0301 1.0000
15.500 1.2685 0.06540 0.06031 0.0115 0.0294 1.0000
15.750 1.2710 0.06796 0.06290 0.0110 0.0287 1.0000
16.000 1.2722 0.07079 0.06577 0.0104 0.0283 1.0000
16.250 1.2743 0.07347 0.06850 0.0098 0.0278 1.0000
16.500 1.2768 0.07608 0.07115 0.0092 0.0273 1.0000
16.750 1.2765 0.07912 0.07424 0.0085 0.0269 1.0000
17.000 1.2775 0.08199 0.07714 0.0078 0.0264 1.0000
17.250 1.2783 0.08491 0.08009 0.0071 0.0260 1.0000
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Polar data table (+)
Polar graphs
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