MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Reynolds number: 200,000 Max Cl/Cd: 60.38 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske1-il-200000-n5.txt Download as CSV file: xf-marske1-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE XM-1D AIRFOIL (F14-3.0)
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5731 0.07580 0.07100 -0.0117 0.6187 0.0382
-9.750 -0.5823 0.07179 0.06692 -0.0132 0.6157 0.0380
-9.500 -0.5960 0.06779 0.06286 -0.0137 0.6126 0.0376
-9.250 -0.6169 0.06360 0.05856 -0.0126 0.6099 0.0373
-9.000 -0.6355 0.05988 0.05468 -0.0102 0.6070 0.0369
-8.750 -0.6501 0.05543 0.04996 -0.0081 0.6042 0.0363
-8.500 -0.6658 0.05012 0.04421 -0.0053 0.6019 0.0355
-8.250 -0.6722 0.04587 0.03946 -0.0023 0.5992 0.0351
-8.000 -0.6662 0.04302 0.03627 -0.0001 0.5952 0.0350
-7.750 -0.6552 0.04065 0.03363 0.0017 0.5905 0.0351
-7.500 -0.6413 0.03860 0.03132 0.0034 0.5858 0.0352
-7.250 -0.6245 0.03693 0.02943 0.0047 0.5815 0.0355
-7.000 -0.6065 0.03532 0.02763 0.0060 0.5764 0.0359
-6.750 -0.5879 0.03375 0.02584 0.0074 0.5711 0.0364
-6.500 -0.5685 0.03222 0.02402 0.0088 0.5662 0.0367
-6.250 -0.5480 0.03075 0.02228 0.0100 0.5612 0.0368
-6.000 -0.5260 0.02938 0.02067 0.0112 0.5549 0.0370
-5.750 -0.5032 0.02815 0.01921 0.0122 0.5492 0.0372
-5.500 -0.4795 0.02704 0.01787 0.0132 0.5440 0.0374
-5.250 -0.4550 0.02603 0.01666 0.0140 0.5373 0.0377
-5.000 -0.4301 0.02512 0.01552 0.0149 0.5313 0.0380
-4.750 -0.4053 0.02440 0.01454 0.0158 0.5249 0.0384
-4.500 -0.3781 0.02337 0.01356 0.0160 0.5171 0.0389
-4.250 -0.3516 0.02259 0.01270 0.0164 0.5107 0.0396
-4.000 -0.3246 0.02188 0.01194 0.0169 0.5029 0.0402
-3.750 -0.2976 0.02120 0.01116 0.0173 0.4960 0.0406
-3.500 -0.2704 0.02058 0.01045 0.0178 0.4894 0.0410
-3.250 -0.2430 0.02001 0.00981 0.0182 0.4816 0.0414
-3.000 -0.2160 0.01950 0.00920 0.0187 0.4748 0.0419
-2.750 -0.1887 0.01907 0.00870 0.0191 0.4672 0.0423
-2.500 -0.1616 0.01848 0.00812 0.0195 0.4603 0.0429
-2.250 -0.1352 0.01795 0.00762 0.0199 0.4546 0.0438
-2.000 -0.1086 0.01755 0.00724 0.0204 0.4481 0.0450
-1.750 -0.0823 0.01722 0.00688 0.0209 0.4417 0.0459
-1.500 -0.0563 0.01695 0.00653 0.0215 0.4362 0.0465
-1.250 -0.0307 0.01655 0.00620 0.0222 0.4301 0.0471
-1.000 -0.0058 0.01618 0.00588 0.0229 0.4246 0.0480
-0.750 0.0192 0.01592 0.00559 0.0236 0.4198 0.0489
-0.500 0.0449 0.01573 0.00539 0.0242 0.4150 0.0503
-0.250 0.0706 0.01552 0.00519 0.0248 0.4096 0.0518
0.000 0.0961 0.01532 0.00497 0.0254 0.4046 0.0534
0.250 0.1221 0.01523 0.00480 0.0260 0.4003 0.0548
0.500 0.1485 0.01515 0.00470 0.0265 0.3961 0.0561
0.750 0.1747 0.01502 0.00458 0.0270 0.3914 0.0582
1.000 0.2010 0.01494 0.00449 0.0275 0.3867 0.0615
1.500 0.2518 0.01474 0.00439 0.0287 0.3792 0.1156
1.750 0.2726 0.01419 0.00444 0.0299 0.3755 0.2804
2.000 0.2781 0.01256 0.00447 0.0343 0.3723 0.7283
2.250 0.3100 0.01250 0.00476 0.0342 0.3680 0.8312
2.500 0.3497 0.01270 0.00501 0.0325 0.3636 0.8845
2.750 0.3872 0.01295 0.00524 0.0310 0.3598 0.9111
3.000 0.4269 0.01320 0.00552 0.0291 0.3557 0.9306
3.250 0.4696 0.01349 0.00580 0.0265 0.3515 0.9468
3.500 0.5091 0.01374 0.00601 0.0245 0.3474 0.9576
3.750 0.5538 0.01403 0.00620 0.0213 0.3435 0.9674
4.000 0.6001 0.01425 0.00644 0.0177 0.3392 0.9748
4.250 0.6349 0.01442 0.00663 0.0163 0.3354 0.9805
4.500 0.6686 0.01456 0.00677 0.0150 0.3319 0.9834
4.750 0.7020 0.01470 0.00688 0.0138 0.3286 0.9862
5.000 0.7343 0.01488 0.00699 0.0128 0.3254 0.9893
5.250 0.7659 0.01506 0.00722 0.0118 0.3219 0.9926
5.500 0.7993 0.01521 0.00743 0.0105 0.3179 0.9952
5.750 0.8324 0.01537 0.00762 0.0093 0.3143 0.9980
6.000 0.8629 0.01553 0.00776 0.0085 0.3106 1.0000
6.250 0.8847 0.01574 0.00791 0.0095 0.3072 1.0000
6.500 0.9064 0.01592 0.00820 0.0105 0.3025 1.0000
6.750 0.9280 0.01610 0.00843 0.0114 0.2975 1.0000
7.000 0.9495 0.01628 0.00860 0.0125 0.2932 1.0000
7.250 0.9707 0.01652 0.00880 0.0135 0.2894 1.0000
7.500 0.9920 0.01677 0.00918 0.0145 0.2854 1.0000
7.750 1.0131 0.01703 0.00950 0.0155 0.2813 1.0000
8.000 1.0341 0.01728 0.00977 0.0166 0.2773 1.0000
8.250 1.0547 0.01755 0.01002 0.0177 0.2737 1.0000
8.500 1.0754 0.01787 0.01044 0.0187 0.2698 1.0000
8.750 1.0958 0.01818 0.01084 0.0197 0.2653 1.0000
9.000 1.1159 0.01848 0.01118 0.0208 0.2608 1.0000
9.250 1.1356 0.01881 0.01149 0.0219 0.2568 1.0000
9.500 1.1552 0.01919 0.01201 0.0230 0.2515 1.0000
9.750 1.1743 0.01956 0.01244 0.0241 0.2463 1.0000
10.000 1.1924 0.01996 0.01280 0.0253 0.2412 1.0000
10.250 1.2106 0.02041 0.01339 0.0264 0.2349 1.0000
10.500 1.2272 0.02089 0.01390 0.0277 0.2284 1.0000
10.750 1.2429 0.02145 0.01452 0.0290 0.2218 1.0000
11.000 1.2568 0.02207 0.01519 0.0304 0.2142 1.0000
11.250 1.2687 0.02280 0.01595 0.0319 0.2070 1.0000
11.500 1.2775 0.02367 0.01686 0.0335 0.1987 1.0000
11.750 1.2826 0.02472 0.01797 0.0353 0.1911 1.0000
12.000 1.2770 0.02618 0.01946 0.0378 0.1839 1.0000
12.250 1.2710 0.02849 0.02183 0.0382 0.1776 1.0000
12.500 1.2656 0.03114 0.02452 0.0379 0.1701 1.0000
12.750 1.2595 0.03389 0.02730 0.0377 0.1633 1.0000
13.000 1.2513 0.03689 0.03032 0.0375 0.1567 1.0000
13.250 1.2418 0.04008 0.03353 0.0371 0.1509 1.0000
13.500 1.2329 0.04333 0.03681 0.0366 0.1454 1.0000
14.000 1.2128 0.05035 0.04390 0.0352 0.1358 1.0000
14.250 1.2024 0.05405 0.04762 0.0343 0.1313 1.0000
14.500 1.1936 0.05773 0.05129 0.0333 0.1277 1.0000
14.750 1.1892 0.06110 0.05475 0.0324 0.1237 1.0000
15.000 1.1836 0.06466 0.05835 0.0313 0.1199 1.0000
15.250 1.1776 0.06829 0.06197 0.0302 0.1165 1.0000
15.500 1.1741 0.07168 0.06540 0.0291 0.1132 1.0000
15.750 1.1706 0.07517 0.06898 0.0279 0.1098 1.0000
16.000 1.1668 0.07870 0.07255 0.0268 0.1065 1.0000
16.250 1.1637 0.08210 0.07593 0.0256 0.1035 1.0000
16.500 1.1609 0.08565 0.07957 0.0243 0.1004 1.0000
16.750 1.1580 0.08925 0.08325 0.0230 0.0973 1.0000
17.000 1.1555 0.09278 0.08681 0.0217 0.0943 1.0000
17.250 1.1543 0.09606 0.09007 0.0205 0.0916 1.0000
17.500 1.1510 0.09990 0.09403 0.0190 0.0888 1.0000
17.750 1.1476 0.10375 0.09796 0.0174 0.0859 1.0000
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Polar data table (+)
Polar graphs
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