UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: UAG 88-143/20 (uag8814320-il) Reynolds number: 1,000,000 Max Cl/Cd: 185.15 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-uag8814320-il-1000000.txt Download as CSV file: xf-uag8814320-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: UAG 88-143/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0719 0.05044 0.04781 -0.1729 0.8039 0.0047
-10.250 -0.0944 0.04608 0.04349 -0.1750 0.8020 0.0046
-10.000 -0.1371 0.04017 0.03750 -0.1730 0.8000 0.0046
-9.750 -0.1814 0.02972 0.02669 -0.1708 0.7981 0.0045
-9.500 -0.1838 0.02685 0.02356 -0.1685 0.7968 0.0045
-9.250 -0.1793 0.02489 0.02137 -0.1662 0.7953 0.0044
-9.000 -0.1722 0.02303 0.01929 -0.1639 0.7943 0.0044
-8.750 -0.1621 0.02138 0.01743 -0.1618 0.7932 0.0044
-8.500 -0.1501 0.01986 0.01568 -0.1599 0.7918 0.0043
-8.250 -0.1400 0.01801 0.01352 -0.1575 0.7904 0.0043
-8.000 -0.1244 0.01668 0.01195 -0.1557 0.7891 0.0043
-7.750 -0.1052 0.01572 0.01082 -0.1545 0.7879 0.0043
-7.500 -0.0847 0.01486 0.00979 -0.1534 0.7868 0.0043
-7.250 -0.0643 0.01392 0.00866 -0.1522 0.7857 0.0044
-7.000 -0.0419 0.01319 0.00777 -0.1514 0.7847 0.0045
-6.750 -0.0185 0.01256 0.00699 -0.1507 0.7838 0.0046
-6.500 0.0061 0.01211 0.00641 -0.1502 0.7828 0.0049
-6.250 0.0300 0.01171 0.00593 -0.1496 0.7816 0.0058
-6.000 0.0545 0.01138 0.00556 -0.1491 0.7805 0.0064
-5.750 0.0792 0.01110 0.00525 -0.1486 0.7792 0.0070
-5.500 0.1039 0.01081 0.00497 -0.1481 0.7778 0.0098
-5.250 0.1292 0.01056 0.00472 -0.1478 0.7764 0.0136
-5.000 0.1556 0.01039 0.00451 -0.1476 0.7751 0.0151
-4.750 0.1819 0.01018 0.00429 -0.1475 0.7739 0.0187
-4.500 0.2086 0.00999 0.00413 -0.1474 0.7728 0.0230
-4.250 0.2359 0.00984 0.00400 -0.1475 0.7717 0.0284
-4.000 0.2636 0.00970 0.00384 -0.1476 0.7706 0.0326
-3.750 0.2913 0.00959 0.00375 -0.1478 0.7695 0.0379
-3.500 0.3186 0.00956 0.00369 -0.1479 0.7682 0.0405
-3.250 0.3436 0.00942 0.00356 -0.1475 0.7668 0.0448
-3.000 0.3693 0.00931 0.00349 -0.1472 0.7651 0.0498
-2.750 0.3959 0.00924 0.00342 -0.1471 0.7634 0.0530
-2.500 0.4224 0.00908 0.00327 -0.1470 0.7618 0.0598
-2.250 0.4497 0.00895 0.00315 -0.1471 0.7603 0.0656
-2.000 0.4772 0.00880 0.00300 -0.1472 0.7590 0.0740
-1.750 0.5048 0.00864 0.00286 -0.1473 0.7576 0.0874
-1.500 0.5319 0.00846 0.00276 -0.1474 0.7562 0.1186
-1.250 0.5555 0.00822 0.00273 -0.1468 0.7543 0.1888
-1.000 0.5783 0.00796 0.00270 -0.1461 0.7522 0.2622
-0.750 0.5998 0.00757 0.00266 -0.1451 0.7500 0.3912
-0.500 0.6192 0.00706 0.00262 -0.1437 0.7479 0.5640
-0.250 0.6364 0.00657 0.00257 -0.1416 0.7458 0.7276
0.000 0.6558 0.00620 0.00258 -0.1396 0.7439 0.8606
0.250 0.7003 0.00615 0.00264 -0.1434 0.7423 0.9328
0.500 0.7453 0.00619 0.00271 -0.1474 0.7402 0.9557
0.750 0.7817 0.00623 0.00274 -0.1494 0.7376 0.9669
1.000 0.8335 0.00632 0.00280 -0.1549 0.7353 0.9766
1.250 0.8786 0.00636 0.00282 -0.1588 0.7329 0.9836
1.500 0.9269 0.00638 0.00279 -0.1636 0.7307 0.9873
1.750 0.9703 0.00643 0.00282 -0.1673 0.7281 0.9917
2.000 1.0083 0.00645 0.00285 -0.1699 0.7248 0.9947
2.250 1.0462 0.00642 0.00283 -0.1725 0.7211 0.9970
2.500 1.0827 0.00639 0.00277 -0.1748 0.7175 0.9990
2.750 1.1122 0.00639 0.00278 -0.1756 0.7136 1.0000
3.000 1.1314 0.00641 0.00282 -0.1741 0.7088 1.0000
3.250 1.1520 0.00643 0.00281 -0.1728 0.7042 1.0000
3.500 1.1711 0.00647 0.00287 -0.1712 0.6992 1.0000
3.750 1.1900 0.00651 0.00292 -0.1696 0.6938 1.0000
4.000 1.2092 0.00657 0.00296 -0.1680 0.6886 1.0000
4.250 1.2267 0.00664 0.00306 -0.1661 0.6823 1.0000
4.500 1.2442 0.00672 0.00312 -0.1642 0.6764 1.0000
4.750 1.2607 0.00681 0.00323 -0.1621 0.6692 1.0000
5.000 1.2753 0.00693 0.00333 -0.1595 0.6618 1.0000
5.250 1.2900 0.00704 0.00347 -0.1570 0.6538 1.0000
5.500 1.3021 0.00719 0.00361 -0.1539 0.6454 1.0000
5.750 1.3104 0.00737 0.00376 -0.1499 0.6353 1.0000
6.000 1.3034 0.00760 0.00394 -0.1427 0.6200 1.0000
6.250 1.3030 0.00788 0.00418 -0.1370 0.6053 1.0000
6.500 1.3067 0.00822 0.00450 -0.1323 0.5922 1.0000
6.750 1.2979 0.00893 0.00511 -0.1255 0.5665 1.0000
7.000 1.2945 0.00979 0.00589 -0.1202 0.5429 1.0000
7.250 1.2911 0.01091 0.00692 -0.1154 0.5177 1.0000
7.500 1.2794 0.01256 0.00837 -0.1096 0.4802 1.0000
7.750 1.2749 0.01397 0.00962 -0.1050 0.4461 1.0000
8.000 1.2663 0.01562 0.01105 -0.1000 0.4049 1.0000
8.250 1.2603 0.01719 0.01240 -0.0955 0.3649 1.0000
8.500 1.2673 0.01818 0.01330 -0.0929 0.3421 1.0000
8.750 1.2514 0.02036 0.01509 -0.0873 0.2786 1.0000
9.000 1.2491 0.02195 0.01645 -0.0837 0.2370 1.0000
9.250 1.2312 0.02450 0.01852 -0.0783 0.1616 1.0000
9.500 1.2200 0.02681 0.02045 -0.0739 0.0999 1.0000
9.750 1.2083 0.02929 0.02258 -0.0697 0.0417 1.0000
10.000 1.2025 0.03151 0.02459 -0.0662 0.0055 1.0000
10.250 1.2139 0.03261 0.02574 -0.0648 0.0043 1.0000
10.500 1.2237 0.03385 0.02707 -0.0632 0.0035 1.0000
10.750 1.2349 0.03502 0.02830 -0.0618 0.0033 1.0000
11.000 1.2459 0.03621 0.02954 -0.0605 0.0031 1.0000
11.250 1.2564 0.03743 0.03082 -0.0592 0.0031 1.0000
11.500 1.2648 0.03887 0.03233 -0.0577 0.0030 1.0000
11.750 1.2728 0.04035 0.03388 -0.0562 0.0029 1.0000
12.000 1.2796 0.04197 0.03557 -0.0547 0.0029 1.0000
12.250 1.2860 0.04365 0.03733 -0.0532 0.0028 1.0000
12.500 1.2908 0.04550 0.03925 -0.0517 0.0028 1.0000
12.750 1.2961 0.04733 0.04117 -0.0503 0.0028 1.0000
13.000 1.2986 0.04948 0.04340 -0.0487 0.0028 1.0000
13.250 1.3026 0.05152 0.04552 -0.0474 0.0027 1.0000
13.500 1.3095 0.05331 0.04736 -0.0464 0.0026 1.0000
13.750 1.3102 0.05571 0.04985 -0.0450 0.0026 1.0000
14.000 1.3122 0.05805 0.05226 -0.0438 0.0025 1.0000
14.250 1.3139 0.06046 0.05474 -0.0427 0.0025 1.0000
14.500 1.3146 0.06302 0.05737 -0.0416 0.0024 1.0000
14.750 1.3142 0.06572 0.06017 -0.0405 0.0025 1.0000
15.000 1.3128 0.06855 0.06308 -0.0394 0.0025 1.0000
15.250 1.3135 0.07118 0.06578 -0.0386 0.0024 1.0000
15.500 1.3146 0.07383 0.06850 -0.0380 0.0023 1.0000
15.750 1.3139 0.07669 0.07144 -0.0371 0.0024 1.0000
16.000 1.3134 0.07950 0.07436 -0.0363 0.0024 1.0000
16.250 1.3132 0.08224 0.07720 -0.0354 0.0025 1.0000
16.500 1.3145 0.08494 0.07997 -0.0350 0.0024 1.0000
16.750 1.3142 0.08784 0.08291 -0.0348 0.0022 1.0000
17.000 1.3159 0.09046 0.08567 -0.0341 0.0024 1.0000
17.250 1.3163 0.09317 0.08848 -0.0334 0.0024 1.0000
17.500 1.3166 0.09595 0.09136 -0.0329 0.0024 1.0000
17.750 1.3150 0.09909 0.09452 -0.0331 0.0022 1.0000
18.000 1.3144 0.10227 0.09784 -0.0331 0.0023 1.0000
18.250 1.3129 0.10537 0.10109 -0.0327 0.0024 1.0000
18.500 1.3105 0.10886 0.10468 -0.0331 0.0024 1.0000
18.750 1.2919 0.11429 0.11054 -0.0318 0.0028 1.0000
19.000 1.3021 0.11630 0.11235 -0.0340 0.0023 1.0000
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