GEMINI (smoothed) (geminism-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GEMINI (smoothed) (geminism-il) Reynolds number: 100,000 Max Cl/Cd: 48.65 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-geminism-il-100000-n5.txt Download as CSV file: xf-geminism-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GEMINI (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5948 0.08648 0.08093 -0.0588 1.0000 0.0363
-12.750 -0.6286 0.07693 0.07125 -0.0653 1.0000 0.0360
-12.500 -0.6589 0.06951 0.06369 -0.0700 1.0000 0.0359
-12.250 -0.6862 0.06372 0.05772 -0.0726 1.0000 0.0358
-12.000 -0.7112 0.05913 0.05294 -0.0734 1.0000 0.0358
-11.750 -0.7344 0.05548 0.04908 -0.0724 1.0000 0.0358
-11.500 -0.7563 0.05257 0.04597 -0.0696 1.0000 0.0360
-11.250 -0.7776 0.05029 0.04349 -0.0652 1.0000 0.0361
-11.000 -0.7962 0.04819 0.04115 -0.0602 1.0000 0.0363
-10.750 -0.8053 0.04611 0.03892 -0.0563 1.0000 0.0367
-10.500 -0.8065 0.04455 0.03732 -0.0530 1.0000 0.0373
-10.250 -0.8072 0.04329 0.03601 -0.0496 1.0000 0.0380
-10.000 -0.8085 0.04209 0.03472 -0.0460 1.0000 0.0388
-9.750 -0.8100 0.04086 0.03336 -0.0421 1.0000 0.0398
-9.500 -0.8108 0.03956 0.03189 -0.0383 1.0000 0.0407
-9.250 -0.8048 0.03795 0.03003 -0.0358 0.9988 0.0419
-9.000 -0.7783 0.03567 0.02732 -0.0370 0.9929 0.0434
-8.750 -0.7497 0.03372 0.02512 -0.0384 0.9871 0.0451
-8.500 -0.7202 0.03239 0.02376 -0.0399 0.9812 0.0473
-8.250 -0.6897 0.03104 0.02225 -0.0413 0.9754 0.0497
-8.000 -0.6582 0.02963 0.02060 -0.0427 0.9697 0.0520
-7.750 -0.6292 0.02833 0.01917 -0.0436 0.9627 0.0545
-7.500 -0.5974 0.02720 0.01806 -0.0453 0.9572 0.0579
-7.250 -0.5693 0.02622 0.01698 -0.0459 0.9494 0.0613
-7.000 -0.5357 0.02517 0.01579 -0.0475 0.9443 0.0650
-6.750 -0.5094 0.02420 0.01485 -0.0479 0.9363 0.0696
-6.500 -0.4769 0.02334 0.01388 -0.0492 0.9305 0.0756
-6.250 -0.4528 0.02246 0.01301 -0.0490 0.9215 0.0814
-6.000 -0.4223 0.02166 0.01214 -0.0500 0.9151 0.0913
-5.750 -0.3991 0.02093 0.01142 -0.0494 0.9053 0.1035
-5.500 -0.3703 0.02002 0.01068 -0.0501 0.8989 0.1269
-5.250 -0.3495 0.01929 0.01017 -0.0491 0.8885 0.1702
-5.000 -0.3211 0.01854 0.00964 -0.0496 0.8821 0.2300
-4.750 -0.3000 0.01804 0.00929 -0.0486 0.8717 0.2769
-4.500 -0.2742 0.01749 0.00891 -0.0483 0.8641 0.3283
-4.250 -0.2515 0.01705 0.00865 -0.0474 0.8547 0.3797
-4.000 -0.2275 0.01668 0.00843 -0.0466 0.8463 0.4334
-3.750 -0.2038 0.01635 0.00828 -0.0456 0.8376 0.4903
-3.500 -0.1816 0.01614 0.00821 -0.0442 0.8286 0.5468
-3.250 -0.1558 0.01595 0.00810 -0.0433 0.8206 0.5920
-3.000 -0.1313 0.01585 0.00801 -0.0423 0.8113 0.6214
-2.750 -0.1022 0.01571 0.00781 -0.0422 0.8036 0.6469
-2.500 -0.0772 0.01565 0.00773 -0.0414 0.7939 0.6699
-2.250 -0.0475 0.01554 0.00755 -0.0414 0.7866 0.6934
-2.000 -0.0220 0.01552 0.00751 -0.0406 0.7765 0.7139
-1.750 0.0086 0.01545 0.00738 -0.0408 0.7690 0.7350
-1.500 0.0352 0.01544 0.00736 -0.0403 0.7591 0.7555
-1.250 0.0651 0.01543 0.00728 -0.0403 0.7509 0.7762
-1.000 0.0956 0.01544 0.00728 -0.0405 0.7417 0.7965
-0.750 0.1267 0.01549 0.00729 -0.0408 0.7328 0.8182
-0.500 0.1581 0.01553 0.00728 -0.0411 0.7241 0.8410
-0.250 0.1920 0.01563 0.00735 -0.0420 0.7144 0.8597
0.000 0.2278 0.01567 0.00730 -0.0433 0.7063 0.8754
0.250 0.2601 0.01576 0.00736 -0.0441 0.6957 0.8905
0.500 0.2981 0.01583 0.00735 -0.0460 0.6866 0.9025
0.750 0.3352 0.01591 0.00737 -0.0479 0.6767 0.9140
1.000 0.3706 0.01600 0.00740 -0.0494 0.6665 0.9260
1.250 0.4068 0.01605 0.00736 -0.0511 0.6577 0.9377
1.500 0.4475 0.01615 0.00743 -0.0539 0.6463 0.9458
1.750 0.4854 0.01624 0.00748 -0.0561 0.6360 0.9550
2.000 0.5232 0.01630 0.00747 -0.0583 0.6265 0.9644
2.250 0.5630 0.01640 0.00757 -0.0611 0.6148 0.9721
2.500 0.6012 0.01649 0.00762 -0.0635 0.6043 0.9809
2.750 0.6393 0.01656 0.00764 -0.0659 0.5944 0.9899
3.000 0.6777 0.01668 0.00778 -0.0686 0.5827 0.9986
3.250 0.7008 0.01679 0.00786 -0.0681 0.5727 1.0000
3.500 0.7201 0.01689 0.00792 -0.0667 0.5636 1.0000
3.750 0.7381 0.01705 0.00810 -0.0651 0.5534 1.0000
4.000 0.7575 0.01719 0.00821 -0.0636 0.5445 1.0000
4.250 0.7760 0.01737 0.00840 -0.0621 0.5347 1.0000
4.500 0.7949 0.01757 0.00859 -0.0605 0.5253 1.0000
4.750 0.8147 0.01776 0.00876 -0.0591 0.5164 1.0000
5.000 0.8331 0.01800 0.00905 -0.0575 0.5067 1.0000
5.250 0.8534 0.01823 0.00924 -0.0562 0.4983 1.0000
5.500 0.8718 0.01850 0.00956 -0.0546 0.4886 1.0000
5.750 0.8915 0.01877 0.00985 -0.0531 0.4798 1.0000
6.000 0.9108 0.01905 0.01015 -0.0516 0.4708 1.0000
6.250 0.9298 0.01936 0.01051 -0.0501 0.4618 1.0000
6.500 0.9499 0.01965 0.01082 -0.0488 0.4534 1.0000
6.750 0.9680 0.02001 0.01126 -0.0471 0.4442 1.0000
7.000 0.9885 0.02032 0.01157 -0.0458 0.4362 1.0000
7.250 1.0049 0.02068 0.01204 -0.0439 0.4256 1.0000
7.500 1.0207 0.02101 0.01242 -0.0418 0.4133 1.0000
7.750 1.0350 0.02134 0.01275 -0.0394 0.3993 1.0000
8.000 1.0477 0.02168 0.01311 -0.0367 0.3843 1.0000
8.250 1.0601 0.02207 0.01352 -0.0341 0.3697 1.0000
8.500 1.0722 0.02249 0.01397 -0.0315 0.3558 1.0000
8.750 1.0828 0.02295 0.01447 -0.0287 0.3411 1.0000
9.000 1.0912 0.02346 0.01502 -0.0256 0.3245 1.0000
9.250 1.0974 0.02403 0.01562 -0.0222 0.3077 1.0000
9.500 1.1014 0.02468 0.01628 -0.0185 0.2892 1.0000
9.750 1.1025 0.02553 0.01707 -0.0147 0.2670 1.0000
10.000 1.1033 0.02658 0.01807 -0.0113 0.2402 1.0000
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Polar data table (+)
Polar graphs
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