E193 (10.22%) (e193-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E193 (10.22%) (e193-il) Reynolds number: 500,000 Max Cl/Cd: 114.15 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e193-il-500000.txt Download as CSV file: xf-e193-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E193 (10.22%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3526 0.08667 0.08449 -0.0382 1.0000 0.0216
-8.500 -0.3559 0.08278 0.08065 -0.0400 1.0000 0.0226
-8.000 -0.3738 0.07554 0.07353 -0.0426 1.0000 0.0233
-7.750 -0.3727 0.07038 0.06842 -0.0484 0.9965 0.0234
-7.500 -0.3561 0.05440 0.05225 -0.0701 0.9851 0.0239
-7.250 -0.3368 0.05080 0.04861 -0.0744 0.9761 0.0245
-7.000 -0.3124 0.04712 0.04483 -0.0791 0.9651 0.0252
-6.750 -0.2876 0.04284 0.04040 -0.0838 0.9503 0.0261
-6.500 -0.2640 0.03788 0.03514 -0.0877 0.9306 0.0280
-6.250 -0.2396 0.03549 0.03208 -0.0884 0.9047 0.0308
-6.000 -0.2342 0.02869 0.02492 -0.0887 0.8805 0.0324
-5.750 -0.2232 0.01954 0.01438 -0.0854 0.8600 0.0181
-4.750 -0.1282 0.01402 0.00776 -0.0822 0.7980 0.0178
-4.500 -0.1043 0.01272 0.00627 -0.0814 0.7854 0.0185
-4.250 -0.0795 0.01192 0.00536 -0.0808 0.7739 0.0191
-4.000 -0.0541 0.01133 0.00466 -0.0803 0.7633 0.0195
-3.750 -0.0283 0.01088 0.00410 -0.0798 0.7533 0.0204
-3.500 -0.0019 0.01049 0.00363 -0.0795 0.7435 0.0217
-3.250 0.0247 0.01020 0.00323 -0.0791 0.7350 0.0232
-3.000 0.0513 0.00983 0.00279 -0.0787 0.7263 0.0273
-2.750 0.0776 0.00937 0.00244 -0.0784 0.7185 0.0615
-2.500 0.1036 0.00899 0.00226 -0.0782 0.7108 0.1253
-2.250 0.1302 0.00872 0.00214 -0.0781 0.7035 0.1813
-2.000 0.1566 0.00846 0.00205 -0.0779 0.6963 0.2454
-1.750 0.1827 0.00815 0.00198 -0.0778 0.6898 0.3341
-1.500 0.2082 0.00778 0.00195 -0.0775 0.6830 0.4462
-1.250 0.2334 0.00749 0.00192 -0.0770 0.6770 0.5482
-1.000 0.2583 0.00719 0.00192 -0.0764 0.6705 0.6484
-0.750 0.2797 0.00680 0.00195 -0.0748 0.6649 0.7904
-0.500 0.3127 0.00654 0.00201 -0.0752 0.6589 0.9383
-0.250 0.3610 0.00658 0.00197 -0.0794 0.6528 0.9819
0.000 0.4126 0.00662 0.00190 -0.0846 0.6471 0.9989
0.250 0.4401 0.00666 0.00189 -0.0846 0.6409 1.0000
0.500 0.4652 0.00675 0.00189 -0.0841 0.6356 1.0000
0.750 0.4906 0.00681 0.00191 -0.0836 0.6301 1.0000
1.000 0.5160 0.00688 0.00193 -0.0831 0.6243 1.0000
1.250 0.5415 0.00699 0.00196 -0.0826 0.6193 1.0000
1.500 0.5672 0.00704 0.00201 -0.0821 0.6135 1.0000
1.750 0.5928 0.00713 0.00205 -0.0816 0.6080 1.0000
2.000 0.6185 0.00723 0.00212 -0.0812 0.6026 1.0000
2.250 0.6443 0.00729 0.00218 -0.0808 0.5963 1.0000
2.500 0.6701 0.00741 0.00224 -0.0803 0.5904 1.0000
2.750 0.6960 0.00747 0.00232 -0.0799 0.5835 1.0000
3.000 0.7218 0.00757 0.00238 -0.0795 0.5768 1.0000
3.250 0.7478 0.00764 0.00248 -0.0791 0.5694 1.0000
3.500 0.7737 0.00774 0.00255 -0.0787 0.5623 1.0000
3.750 0.7997 0.00781 0.00264 -0.0784 0.5542 1.0000
4.250 0.8516 0.00800 0.00285 -0.0776 0.5376 1.0000
4.500 0.8775 0.00811 0.00296 -0.0772 0.5291 1.0000
4.750 0.9033 0.00822 0.00308 -0.0768 0.5195 1.0000
5.000 0.9291 0.00832 0.00322 -0.0765 0.5092 1.0000
5.250 0.9547 0.00845 0.00336 -0.0760 0.4982 1.0000
5.500 0.9794 0.00858 0.00348 -0.0754 0.4797 1.0000
5.750 1.0032 0.00879 0.00363 -0.0747 0.4549 1.0000
6.000 1.0267 0.00904 0.00383 -0.0740 0.4304 1.0000
6.250 1.0495 0.00937 0.00407 -0.0732 0.3982 1.0000
6.500 1.0685 0.00999 0.00443 -0.0718 0.3416 1.0000
6.750 1.0844 0.01089 0.00498 -0.0700 0.2737 1.0000
7.000 1.1003 0.01181 0.00561 -0.0683 0.2151 1.0000
7.250 1.1155 0.01278 0.00627 -0.0666 0.1611 1.0000
7.500 1.1317 0.01363 0.00691 -0.0649 0.1203 1.0000
7.750 1.1458 0.01460 0.00763 -0.0630 0.0784 1.0000
8.000 1.1548 0.01591 0.00861 -0.0603 0.0325 1.0000
8.250 1.1673 0.01690 0.00953 -0.0580 0.0187 1.0000
8.500 1.1826 0.01764 0.01031 -0.0561 0.0160 1.0000
8.750 1.1980 0.01830 0.01103 -0.0542 0.0147 1.0000
9.000 1.2094 0.01905 0.01184 -0.0517 0.0138 1.0000
9.250 1.2174 0.01996 0.01282 -0.0487 0.0130 1.0000
9.500 1.2219 0.02110 0.01406 -0.0455 0.0125 1.0000
9.750 1.2271 0.02227 0.01533 -0.0426 0.0123 1.0000
10.000 1.2345 0.02337 0.01652 -0.0403 0.0120 1.0000
10.250 1.2409 0.02461 0.01786 -0.0380 0.0118 1.0000
10.500 1.2456 0.02606 0.01940 -0.0358 0.0116 1.0000
10.750 1.2503 0.02762 0.02105 -0.0339 0.0113 1.0000
11.000 1.2552 0.02927 0.02279 -0.0322 0.0111 1.0000
11.250 1.2592 0.03110 0.02472 -0.0306 0.0109 1.0000
11.500 1.2635 0.03299 0.02670 -0.0291 0.0108 1.0000
11.750 1.2686 0.03491 0.02873 -0.0278 0.0109 1.0000
12.000 1.2737 0.03687 0.03079 -0.0266 0.0105 1.0000
12.250 1.2802 0.03872 0.03272 -0.0257 0.0103 1.0000
12.500 1.2854 0.04083 0.03492 -0.0247 0.0101 1.0000
12.750 1.2909 0.04285 0.03701 -0.0240 0.0099 1.0000
13.000 1.2962 0.04512 0.03940 -0.0230 0.0098 1.0000
13.250 1.3010 0.04742 0.04180 -0.0223 0.0097 1.0000
13.500 1.3056 0.04986 0.04438 -0.0215 0.0097 1.0000
13.750 1.3090 0.05252 0.04717 -0.0209 0.0096 1.0000
14.000 1.3108 0.05539 0.05021 -0.0204 0.0096 1.0000
14.250 1.3107 0.05857 0.05356 -0.0202 0.0096 1.0000
14.500 1.3087 0.06202 0.05717 -0.0201 0.0095 1.0000
14.750 1.3047 0.06577 0.06109 -0.0203 0.0095 1.0000
15.000 1.2973 0.07009 0.06563 -0.0209 0.0095 1.0000
15.250 1.2881 0.07478 0.07053 -0.0220 0.0096 1.0000
15.500 1.2738 0.08059 0.07663 -0.0234 0.0099 1.0000
15.750 1.2460 0.08897 0.08537 -0.0265 0.0102 1.0000
16.000 1.2206 0.09741 0.09410 -0.0303 0.0104 1.0000
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Polar data table (+)
Polar graphs
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